Abstract: A piloting device (1) for piloting a vehicle, in particular an aircraft, has a frame (10), a cradle (20) pivoting with respect to the frame on a first pivot axis (R), a piloting member, called a stick (30), pivoting with respect to the cradle (20) on a second axis (T) orthogonal to and intersecting the first axis, first return elements (11,11?,12) for returning the cradle to a predetermined position with respect to the frame, called the neutral position of the cradle, second return elements (21,21?,22) for returning the stick to a predetermined position with respect to the cradle, called the neutral position of the stick, wherein at least one of the second return elements, called a stick jack (22), is arranged between the stick and the frame.

Abstract: A process and device for controlling a synchronous motor driving an operating lever in opposition to a friction brake, including a sensor for sensing the position of the lever, and a control computer include: a first regulator defining a nominal control voltage (U*) as a function of a difference (??) between the speed of rotation (?_feedback) of the motor and a set-point speed (?_cmd); a second regulator determining saturation limits (?Usat; +Usat) of the nominal control voltage as a function of an instantaneous torque provided by the motor; a saturator providing a limited control voltage (U_cmd) on the basis of the nominal control voltage and on the basis of the saturation limits; a converter feeding each winding of the motor with an alternating-voltage signal (U_alim) worked out on the basis of the limited control voltage as a function of the angular position of the motor.

Abstract: A device for combining force between two control units includes force feedback, each control unit including a control stick (21, 31) and at least one force sensor (24, 34) suitable for providing a value of the control force (Fp, Fcp) exerted by a pilot, the device being suitable for forming a force feedback value from the sum of the values of the control forces of each control unit. A correction device limits the force feedback value (Fcor_p) according to at least one parameter taken from the absolute value of the control force (Fcp) of the second control unit and the difference between the control force values of each control unit. A control unit including such a device for combining forces, and an aircraft provided with such control units are also described.

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 piloting device for piloting an aircraft includes a piloting member (11), a mechanism (13) for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame (12), stops (25, 26, 35) arranged so as to cooperate with bearing surfaces (32) integral with the piloting member upstream of the mechanism in order to limit the rotation amplitude thereof, and at least one force sensor (19), these being arranged with respect to one another so that each contact of a bearing surface (32) with a stop (25, 26, 35) generates an abutment reaction, the orientation of which with respect to each deformable sensing element of each force sensor is such that it stresses this deformable sensing element at least substantially outside its deformation modes.

Abstract: An electronic operational control device for an aircraft piloting device with two connected piloting members, includes electronic circuits for main monitoring from signals delivered by sensors associated with one of the piloting members, and at least one electronic circuit (52 to 55) for cross-monitoring, for digital processing of signals delivered by sensors (83, 93) associated with the other piloting member, adapted to detect any deviation of these signals corresponding to a fault and to generate a signal representing such a fault. A piloting device and an aircraft including such an electronic operational control device with cross-monitoring are also disclosed.

Abstract: A piloting device (1) for piloting a vehicle, in particular an aircraft, has a frame (10), a cradle (20) pivoting with respect to the frame on a first pivot axis (R), a piloting member, called a stick (30), pivoting with respect to the cradle (20) on a second axis (T) orthogonal to and intersecting the first axis, first return elements (11,11?,12) for returning the cradle to a predetermined position with respect to the frame, called the neutral position of the cradle, second return elements (21,21?,22) for returning the stick to a predetermined position with respect to the cradle, called the neutral position of the stick, wherein at least one of the second return elements, called a stick jack (22), is arranged between the stick and the frame.

Abstract: A piloting device for piloting an aircraft includes a piloting member (11), a mechanism (13) for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame (12), stops (25, 26, 35) arranged so as to cooperate with bearing surfaces (32) integral with the piloting member upstream of the mechanism in order to limit the rotation amplitude thereof, and at least one force sensor (19), these being arranged with respect to one another so that each contact of a bearing surface (32) with a stop (25, 26, 35) generates an abutment reaction, the orientation of which with respect to each deformable sensing element of each force sensor is such that it stresses this deformable sensing element at least substantially outside its deformation modes.

Abstract: The invention relates to a piloting device comprising a piloting component (10) which is connected to at least one steering component (13), at least one force sensor (17) which measures the forces imparted into the kinematic chain (12) by said piloting component (10), a logic circuit (23) which is adapted to develop a speed reference signal according to a predetermined function of said force signals, and a circuit for controlling at least one parallel actuator (14) as regards speed. It extends to a method for the motorised assistance and control of a device of this kind and to an aircraft comprising a device of this kind.

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: The invention relates to a device for piloting an aircraft, having at least one piloting member which is movable about at least one axis of rotation equipped with at least one contactless angular position sensor including a stator assembly and a rotor assembly which are movable in relation to one another about an axis of rotation, at least one magnetic-field-sensitive element which is radially offset in relation to the axis of rotation, interlinked on one of the assemblies and placed opposite the magnetic structure interlinked on the other of the assemblies, and comprises: a plurality of Hall effect detecting cells, a supply and measuring circuitry which is configured for selecting, for each detecting cell supplied with power, a predetermined value of a compensation coefficient Gk depending on the position in relation to the axis of rotation of this powered detecting cell, and for applying this compensation coefficient value Gk by modifying at least one intensity and/or voltage signal, such that errors cau

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: The invention relates to a device for piloting an aircraft, having at least one piloting member which is movable about at least one axis of rotation equipped with at least one contactless angular position sensor including a stator assembly and a rotor assembly which are movable in relation to one another about an axis of rotation, at least one magnetic-field-sensitive element which is radially offset in relation to the axis of rotation, interlinked on one of the assemblies and placed opposite the magnetic structure interlinked on the other of the assemblies, and comprises: a plurality of Hall effect detecting cells, a supply and measuring circuitry which is configured for selecting, for each detecting cell supplied with power, a predetermined value of a compensation coefficient Gk depending on the position in relation to the axis of rotation of this powered detecting cell, and for applying this compensation coefficient value Gk by modifying at least one intensity and/or voltage signal, such that errors cau

Abstract: An electronic control device for an aircraft piloting member mounted on an electromechanical supporting box (23, 24) includes at least one actuating motor on at least one degree of freedom, and sensors associated with the piloting member to detect at least the position thereof on each degree of freedom. A command/monitoring unit (47, 48) of the piloting member has at least one electronic microcontroller (52 to 55) adapted to: command at least one motor on one degree of freedom, receive signals of sensors (83, 93) on another degree of freedom, carry out monitoring of the signals to detect any deviation thereof. A piloting device and an aircraft including such an electronic control device are also disclosed.

Abstract: An electronic operational control device for an aircraft piloting device with two connected piloting members, includes electronic circuits for main monitoring from signals delivered by sensors associated with one of the piloting members, and at least one electronic circuit (52 to 55) for cross-monitoring, for digital processing of signals delivered by sensors (83, 93) associated with the other piloting member, adapted to detect any deviation of these signals corresponding to a fault and to generate a signal representing such a fault. A piloting device and an aircraft including such an electronic operational control device with cross-monitoring are also disclosed.

Abstract: The invention relates to a piloting device comprising a piloting component (10) which is connected to at least one steering component (13), at least one force sensor (17) which measures the forces imparted into the kinematic chain (12) by said piloting component (10), a logic circuit (23) which is adapted to develop a speed reference signal according to a predetermined function of said force signals, and a circuit for controlling at least one parallel actuator (14) as regards speed. It extends to a method for the motorised assistance and control of a device of this kind and to an aircraft comprising a device of this kind.