Abstract: A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

Abstract: A wing for an aircraft is disclosed including a fixed wing, a high-lift device and a hold-down arrangement arranged between two supports of the high lift device having a first hold-down element attached to the high-lift device and a second hold-down element attached to the fixed wing. The first hold-down element contacts the second hold-down element when the high-lift device is in a retracted position in which it prevents a trailing edge of the high-lift device from detaching from an upper surface of the fixed wing when the fixed wing deforms in the spanwise direction. One of the hold-down elements is a load-limited hold-down element which comprises a hydraulic element that is configured to allow the high-lift device to move away from the fixed wing when a load acting through the hold-down arrangement exceeds an operational threshold.

Abstract: In an aspect, a cockpit assembly is presented. A cockpit assembly includes at least a door. A cockpit assembly includes an inceptor stick. An inceptor stick includes a sheath movably connected thereon. An inceptor stick includes an actuator communicatively connected to a sheath. An actuator is configured to move a sheath between at least a door of a cockpit and an inceptor stick.

Abstract: A system may include an electromagnetic load, a driver configured to drive the electromagnetic load with a driving signal, and a processing system communicatively coupled to the electromagnetic load and configured to, during a haptic mode of the system couple a first terminal of the electromagnetic load to a ground voltage and cause the driving signal to have a first slew rate, and during a load sensing mode of the system for sensing a current associated with the electromagnetic load, couple the first terminal to a current-sensing circuit having a sense resistor coupled between the first terminal and an electrical node driven to a common-mode voltage and cause the driving signal to have a second slew rate lower than the first slew rate.

Abstract: A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

Abstract: Disclosed is a throttle quadrant arrangement utilizing a throttle lever mechanically connected to three Rotary Variable Differential Transformers (RVDTs). The signals from the RVDTs are monitored by a process where the processing component. More specifically, RVDT outputs are monitored by the engine control system to determine if they are outside a predetermined range of operability. If an RVDT is not operable, the engine control system establishes a thrust output using the signal from one of the functional two. If only one or none are within the range, the system moves on to a default mode.

Abstract: A technique for control loading employs a slotted motor having a higher power density than comparably-powerful slotless motors. The use of smaller slotted motors enables more efficient mounting hardware, smaller gear reduction mechanisms, and more efficiently mounted force transducers. The technique overcomes cogging and smooths torque response of the slotted motor by combining high-gain servo control with high-resolution motor sensing.

Abstract: A system for producing a control signal of an electric vertical take-off and landing (eVTOL) aircraft includes a flight controller configured to obtain a requested aircraft force, generate an optimal command mix, wherein the optimal command mix includes a plurality of commands to a plurality of actuators as a function of the requested aircraft force, wherein generating further comprises receiving an ideal actuator model includes at least a performance parameter, producing a model datum as a function of the ideal actuator model, and generating the optimal command mix as a function of the request aircraft force and the model datum, and produce a control signal as a function of the optimal command mix.

Abstract: Systems and methods for hydraulic droop control of an aircraft wing. One embodiment is a hydraulic droop panel system for an aircraft wing. The hydraulic droop panel system includes a first hydraulic actuator attached to a flap of the aircraft wing, and a second hydraulic actuator attached to a droop panel of the aircraft wing and fluidly coupled with the first hydraulic actuator. The second hydraulic actuator is configured to move the droop panel to a droop position corresponding with movement of the flap and the first hydraulic actuator.

Abstract: The invention relates to a system for controlling a work machine, in particular a wheel loader, having at least one hand-held control device (6), in particular a joystick or steering wheel, at least one restoring device (8) in the form of one or more spring assemblies, which are connected to the hand-held control device in such a way a restoring force is exerted upon the hand-held control device by the spring assembly when said spring assembly is not in the central position. An adjusting device (9, 12, 13) which engages with the spring assembly such that an adjustment of the central position of the spring assembly can be carried out, is provided.

Abstract: An aircraft control system includes pilot and co-pilot flight control systems that each include a first shaft mechanically coupled to and displaced apart from a second shaft, the shafts defining and being rotatable about independent longitudinal axes. A connecting link enables rotation of one of the first shafts to rotate a corresponding one of the second shafts. A position transducer is mechanically coupled to each shaft and configured to communicate an electrical signal corresponding to the rotation of the respective shaft. A flight control unit electrically communicates with the position transducers and is configured to (a) receive the electrical signal from each position transducer, (b) detect a failure of the flight control system by detecting differences in the position transducers' electrical signals, and (c) communicate the electrical signal from the position transducer to a flight control surface actuation system to compensate for the detected failure.

Abstract: An improved method and circuitry for fluid power applications that provides energy savings through the sequential recycling of normally exhausted pressure or vacuum by direct transfer and accumulation of exhaust pressure for additional use, including from one end of the actuator to the opposite end or within the actuator itself and for use by other devices in separate systems.

Abstract: Described herein is an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.

Abstract: A device for managing the mechanical energy of an aircraft, with a force application system on a control lever, includes a support defining a guide; a moving control lever for controlling varying a mechanical energy variation of the aircraft, mounted moving through the guide; and at least one position sensor detecting the position of the moving lever in the guide, configured to create position information for the position of the moving lever in the guide intended to be sent to a flight control unit of the aircraft. The device also includes an active force applicator for applying a force on the moving lever, configured to generate a force applied on the moving lever. The force depends on the position of the moving lever in the guide.

Abstract: An autopilot system includes an actuator arrangement that receives control signals to influence the flight of the helicopter in a selected one of a plurality of different flight modes. A control stick input arrangement allows flight mode selection and control with no more than a particular one of the pilot's hands in the engaged position on the stick and without moving the hand away from the engaged position. A slaved gyro output signal is based on no more than the set of sensor outputs used by the autopilot such that an autopilot display presents autopilot flight mode information while displaying a slaved gyro output. The autopilot provides for pilot selection of one of a subset of the plurality of flight modes which is customized based on a current flight status of the helicopter. An automatic autorotation mode is provided.

Abstract: An electronic gaming machine (EGM) includes a programmable haptic interface that produces, responsive to a force feedback signal, a variable amount of resistance to movement of a moveable element of the programmable haptic interface by a player as a haptic force feedback. A memory is coupled to a processor circuit and includes machine-readable instructions that cause the processor circuit to initiate a wagering game on the EGM. The processor circuit further generates the force feedback signal controlling an amount of resistance to movement of the moveable element of the programmable haptic interface based on a game event in the sequence of game events. The programmable haptic interface includes a magnetorheological fluid coupling the moveable element to a fixed housing that is mounted to the EGM and a circuit controlling a magnitude of a magnetic field that is applied across the magnetorheological fluid responsive to the force feedback signal.

Abstract: An operation device includes an operation unit including an operation body worked by an operator's manipulation; a position detecting part detecting a position of the operation body; and a display unit displaying a position of the operation body. The display unit includes an operation member, a supporting body, and a movable load applying mechanism including a movable member, a magnetic generating mechanism, a magnetorheological fluid, and an operation controlling part. The display unit includes a display part displaying the operation position. A display controlling part PS controls a display. A controller is included to control the operation controlling part and the display controlling part. In a control method of the operation device, the controller controls to display a state of the operation position of the operation body on the display part.

Abstract: A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

Abstract: A method and a device for coupling piloting members (20, 50), wherein saturation values (SCpsat?, SCpsat+, SCcopsat?, SCcopsat+) of at least one force saturator (28, 58) are adapted such that a force-feedback is exerted for each of these saturation values at a force-feedback value, taken at the force application centre of the manoeuvring handle (21, 51), of between 4 daN and 40 daN, with the result that a function of disconnecting is at least in part performed by the at least one force saturator.

Abstract: A method of determining the state of a pedal actuator system within a vehicle includes receiving a position sensor signal indicative of a position of an actuator pedal within the pedal actuator system, receiving a force sensor signal indicative of a compressive force applied to the actuator pedal, and determining, with a processor, a state of the actuator pedal based on the position sensor signal and the force sensor signal. The state of the actuator pedal is one of a normal operating state and a fault state.

Abstract: An improved method and circuitry for fluid power applications that provides energy savings through the recycling of normally exhausted pressure by direct transfer and accumulation of exhaust pressure for additional use, including from one end of the actuator to the opposite end or within the actuator itself and for use by other devices in separate systems.

Abstract: An active inceptor apparatus and method for operating a machine. The apparatus comprises a stick member having a grip portion, the stick member being pivotably mounted relative to a housing. It further comprises a position sensor responsive to, and for generating signals indicative of, stick member position. A force sensor is provided on the stick member responsive to, and for generating signals indicative of, force applied to the stick by a user. The apparatus also includes a control unit operable to receive the position and force signals from the position and force sensors respectively. The control unit is operable to process the signals according to a predetermined relationship to determine a value FD indicative of force applied to the stick member relative to displacement of the stick member. The control unit is also operable to generate machine control signals as a function of position signals and force signals in dependence upon the value FD, for communication to the machine.

Abstract: A user-input device includes a user-actuatable trigger configured to pivot about a trigger axis, the user-actuatable trigger including a sector gear, a posture sensor configured to determine a posture of the user-actuatable trigger about the trigger axis, and a force-feedback motor configured to drive the sector gear based on a force-feedback signal.

Abstract: A brushless motor drive device includes the following: an inverter circuit configured to energize and drive the winding of a brushless motor; a current detection circuit configured to detect the current value of the winding; a control unit configured to control the rotation of the motor; and an RC filter including a resistor and a capacitor. The control unit includes the following: a drive control unit configured to generate a signal to drive the inverter; a clock generation circuit configured to generate a clock pulse to be used as a reference for an operation period; a pulse output circuit configured to generate a pulse signal with a changing frequency based on the clock pulse and to apply the pulse signal to the RC filter; an AD converter circuit connected to the capacitor of the RC filter and the current detection circuit; and an AD-conversion-error calculation unit configured to calculate the conversion error of the AD converter circuit.

Abstract: The subject matter of this specification can be embodied in, among other things, a motion control apparatus that includes a brushless DC motor to actuate a mechanical output based on a collection of phase power signals, a collection of first Hall effect sensors configured to provide a collection of first feedback signals in response to a sensed motor position and a sensed motor speed, a controller configured to determine a speed and position of the motor based on the feedback signals, and determine an electrical current level based on a collection of operational parameters and feedback signals including a position of the mechanical output, the motor speed, and the motor position, a current controller configured to provide electrical phase sequence output signals based on the electrical current level, and a motor driver configured to provide the collection of phase power signals based on the electrical phase sequence output signals.

Abstract: A force feedback cuff system, method, and apparatus may include receiving force feedback signal from an external, remotely controlled device; processing the force feedback signal to determine a correlated amount of pressure; applying a correlated signal to air pump equipment to inflate or deflate an inflatable cuff on an operator; and continuing the receiving, processing, and applying while the operator controls the external, remotely controlled device to provide haptic feedback to the operator in an intuitive and non-obtrusive fashion.

Abstract: The invention relates to a flight control device for an aircraft, including a connection lever, mechanical means for limiting an angular stroke of the connection lever, first means for generating force feedback on the connection lever about said pivot axis, second means for generating force feedback on the connection lever, which means are arranged in parallel with the first means, at least one element selected from the second means and the connection lever comprising mechanical means for connecting them together temporarily, which means are arranged to be active when the connection lever is moved beyond a predetermined angular position in the angular range so that the second means are connected to the connection lever.

Abstract: A system and method for displaying standby instrument information is disclosed. The touch-screen instrument panel system for a vehicle has a touch-screen information panel display configured to display vehicle operation information received from a computing system and a standby instrument display that is secured to an area located behind the information panel display. The standby instrument display is hidden from view when the information panel display is in a powered state but is in full view when the information panel display is in an unpowered state.

Abstract: A control system for controlling a rotorcraft rotor, to a rotorcraft fitted therewith, and to a corresponding control method. The system comprises selector means for defining at least two disjoint position ranges for the control member between two physical abutments corresponding to the movement limits of the control member, a first position range being defined between at least two first limit values about a zero force position of the control member, and at least one second position range being defined between at least one of the at least two first limit values and at least one second limit value; and control means for allocating a first control law to the first position range of the control member and a second control law to the second position range of the control member, the first and second control laws being selected to be mutually distinct.

Abstract: Example methods and systems are disclosed for performing automated tasks with a robot system. In one example, a robot system includes a robotic arm and an end-effector coupled to the robotic arm. The end-effector is actuatable among more than two states of actuation. The robot system also includes an analog control switch located on the end-effector. The analog control switch is actuatable among more than two switch positions. The analog control switch is configured such that actuation of the analog control switch among the more than two switch positions causes a corresponding actuation of the end-effector among the more than two states of actuation.

Abstract: A method and device for displaying at least one position indicator for an aircraft. The display device includes at least one unit for generating information for determining, during a flight of the aircraft, a control value representative of the movement by a first pilot of his joystick relative to at least one of the roll and pitch axes of the aircraft, at least one computation unit for computing a piloting command representative of the control value determined by the unit for generating information, and one display unit for displaying at least one symbol on at least one screen intended for the second pilot and directly visible by the latter, the symbol representing the position indicator and being displayed on the screen in a position illustrating the piloting command on the screen.

Abstract: One illustrative system disclosed herein includes a processor configured to: receive a signal; determine a haptic effect based at least in part on the signal; and transmit a haptic signal associated with the haptic effect. The system further includes a haptic output device in communication with the processor and coupled to a holder, wherein the holder is configured to mechanically couple with an electronic device. The haptic output device is configured to receive the haptic signal and output the haptic effect.

Abstract: Electrical distribution system for an aircraft comprising at least one electrical supply path comprising at least one power unit capable of opening or closing the connection between at least one electrical energy source and at least one device of the aircraft. The system comprises protection cards (2b, 2n) each comprising at least two microcontrollers each capable of sending a command to each power unit of the electrical supply paths protected by each protection card and, among the set of microcontrollers of the protection cards, at least two microcontrollers are provided with a communication and computation function with all of the microcontrollers of the protection cards (2b, 2n).

Abstract: The invention relates to a control device (2) for controlling a vehicle having an electric motor (1), the control device comprising a control system (21, 22, 23) provided with one or more levers movable between a minimum control position and a maximum control position, and a control unit (3) for controlling the motor. Said control unit (3) includes acquisition means (31) for acquiring a signal representative of the position of said control system, determination means (32) for determining a setpoint speed value corresponding to said acquired signal, as a function of a maximum setpoint speed value associated with the maximum control position, and control means (33) for controlling the motor as a function of the determined setpoint speed. Said control device has adjustment means (34) arranged with the lever(s) of the system to enable the maximum setpoint speed value to be adjusted without taking a hand away from the lever(s). The invention also provides a corresponding vehicle.

Abstract: An actuator system having a controlled element configured for rotary movement about a first axis relative to a reference structure; a linkage system between the element and reference structure; a first actuator and a second actuator configured to power a first degree of freedom and an independent second degree of freedom of the linkage system, respectively; the linkage system having a first link configured for rotary movement about a second axis not coincident to the first axis and second link configured for rotary movement about a third axis; the linkage system configured such that a first angle of rotation may be driven independently of a second angle of rotation between said first link and said reference structure; wherein one of the first or second actuators is configured and arranged to drive rotation of the element about the first axis when the other is operatively locked.

Abstract: A method for operating a mechanical flight control system is provided. The method provides a torque command to a servo torque control loop, wherein the servo torque control loop comprises at least one position control servo; receives at least one feedback signal from the position control servo, during operation of the position control servo; detects user external load disturbance input to the servo torque control loop, based on the at least one feedback signal; and adjusts operation of the position control servo, based on the detected user external load disturbance input.

Abstract: The invention concerns a device for the active control of a force feedback for a control device, comprising a calculator, a position sensor (3) configured to provide the calculator with an effective position signal (Pm) of the control device, and an actuator (2) ensuring the displacement of the control device at the command of the calculator, the calculator being configured to use the effective position signal and modulate a setpoint current (lc) delivered to the actuator to ensure the position feedback of the displacement of the control device, characterized in that the calculator is further configured to create at least one saturation terminal (Bsat+, Bsat?) according to a predetermined function of the value of the effective position signal of the position/force law kind, and to saturate the setpoint current using the at least one saturation terminal.

Abstract: An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections.

Abstract: A control lever (10) provided with a stick (11) extending axially from a stand (11?) towards grip means (11?) and with a carrier structure (20) for said stick (11) that is hinged about a first hinge axis (AX1) and about a second hinge axis (AX2). The control lever (10) includes phasing means (30) constrained to move in rotation with said stick (11) about said first hinge axis (AX1) and about said second hinge axis (AX2), said phasing means (30) comprising at least three main arms (31, 32, 33), each for controlling a respective power member (8?, 8?, 8??) that is connected to a set (6) of swashplates for controlling a rotary wing (2).

Abstract: An actuator system having a controlled element configured for rotary movement about a first axis relative to a reference structure; a linkage system between the element and reference structure; a first actuator and a second actuator configured to power a first degree of freedom and an independent second degree of freedom of the linkage system, respectively; the linkage system having a first link configured for rotary movement about a second axis not coincident to the first axis and second link configured for rotary movement about a third axis; the linkage system configured such that a first angle of rotation may be driven independently of a second angle of rotation between said first link and said reference structure; wherein one of the first or second actuators is configured and arranged to drive rotation of the element about the first axis when the other is operatively locked.

Abstract: The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).

Abstract: A method for monitoring an aircraft piloting device including at least one piloting member (20, 30) and at least one fly-by-wire flight control system (40, 41). At least one monitoring module is integrated into this control system and is adapted to compute, on the basis of primary signals processed by sensors associated with at least one piloting member, at least one theoretical value of at least one monitored parameter of at least one piloting member, to compare each theoretical value with measurement signals of each monitored parameter and to select a monitoring action, particularly to generate monitoring signals (55, 56), as a function of the difference between each theoretical value and the measurement signals.

Abstract: A device for generating a return force for a control stick that is movable from a neutral position along a travel path, includes a mechanical connection member connecting the stick to a resilient return member for returning the stick towards the neutral position. The mechanical connection member and the resilient return member produce, over a first portion of the travel path, a first strength of return force and, over a second portion of the travel path, a second strength of return force. A transmission part is mechanically connected to the stick so that any stick movement along the second portion corresponds to turning movement of the transmission part, and so that the return force to the stick is transmitted to the stick positioned in the second portion.

Abstract: A mechanical control mixer configured to couple to an aircraft is provided. An axle is mounted to a frame of the mechanical control mixer, and a barrel is configured to rotate about the axle. A central rod is disposed within the barrel. The central rod is configured to rotate with respect to the barrel. A roll control input is connected to the central rod. The roll control input is configured to cause the central rod to rotate within the barrel. Output control rods are connected to the central rod. The output control rods are connected to at least one control surface of the aircraft. An air brake input is connected to the barrel. The air brake input is configured to cause the barrel to rotate about the axle to move at least one of the output control rods.

Abstract: The subject of the invention is a control unit (A), which comprises actuation units (F) such as a rudder and brakes for a pilot in an aircraft, which comprises a rotating shaft (2) mobile in rotation around an axis (40); said shaft is driven in rotation when the pilot performs an action on the actuation units (F), in particular the brake pedals, by mechanical transmission between said shaft and said actuation units, and which comprises a device for generating resistive torque (1) designed to be fastened along the rotating axis of the control unit; the device for generating resistive torque comprises a friction disk (3, 4, 5) mounted axially and fastened to the rotating axle (2), a first annular track (6, 7, 8) fastened to a frame element (9) of the control unit; and means of support (10, 11, 12).

Abstract: An improved flight control system is described, providing for increased or reduced pilot input forces necessary to cause desired control surface deflections.

Abstract: A aircraft control system is provided that provides tactile feedback between control columns of the aircraft relating to discrepancies in the control inputs to the sticks of the respective control columns. In one implementation, the sticks each have an associated feedback assembly that is adjustable relative to mechanical ground to adjust the feedback profile applied to the corresponding stick. The position of each feedback assembly is adjusted based on a relative displacement between the other feedback assembly and its corresponding stick to provide active feedback relating to the control of the other control column.

Abstract: An actuator which can be installed in a system for the virtual simulation of aircraft, ships and vehicles to help the system with the controls. More specifically, the invention is an actuator used for a control loading system, which can be installed into a virtual simulation system, receive force delivered by the movement of a control stick laterally while measuring the applied force. It can connect a lever which delivers the control force equivalent to the applied force and reaction force by making use of a direct drive motor, including a potentiometer which senses the angle of rotation while sensing the initial reference position separately from an encoder, limiting the rotation range of the rotating lever, fixing the initial neutral position, and the control loading system for actuators manufactured compactly on the whole.

Abstract: A control system for an aircraft including a passive feedback arrangement, a stick and a positioning arrangement is provided that provides for user adjustability of the resistance applied to the stick, such as in a fly-by-wire system. The passive feedback arrangement is movable relative to a mechanical ground. The stick is moveable relative to the mechanical ground and the passive feedback arrangement. The passive feedback arrangement acts on the stick to resist movement of the stick relative to the passive feedback arrangement. This resistance provides passive feedback to the pilot for the fly-by-wire system. The positioning arrangement is coupled to the passive feedback arrangement for adjusting the position of the passive feedback arrangement relative to the mechanical ground in response to movement of the stick relative to the mechanical ground.

Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated.