Ratier Figeac

Ratier-figeac Sas

Cedric Antraygue

Bruno Seminel

Arnaud Soulié

Arnaud Delpeuch

A piloting device for piloting an aircraft includes a piloting member suitable for being actuated by a pilot, a mechanism for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame, at least one force sensor connected between the piloting member. The mechanism includes at least one sensing element configured to produce a signal upon deformation indicative of a force applied to the piloting member. The force sensor comprises at least one pair of bearing surfaces. The device also includes at least one pair of stops configured to limit the angular amplitude of rotation of the piloting member with respect to the frame on abutment of the at least one pair of bearing surfaces with at least one pair of stops. The stops or at least one of the bearing surfaces comprises a compliant material.

Stops for force sensor

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.

Cockpit inceptor system

A method and system for simulating pilot controls in a cockpit simulator by controlling one or more arms on which is/are mounted a control grip, pedal or the like, to locate the grip at different positions and allow movement of the grip in a plurality of movement directions and trajectories while allowing varying force feedback.

Cockpit controls simulation

A flight control actuator for actuating an aircraft flight control system is provided. The flight control actuator comprises a gearbox, an output shaft attached to the gearbox and an output lever provided on the output shaft. The output lever is declutchable from the output shaft. The output lever includes an inner diameter through which the output shaft passes and at least one indentation in said inner diameter. The output shaft includes a hollow cylindrical member with at least one hole provided at the axial position of the at least one indentation of the output lever.

Actuator with declutchable output lever

A method and a device for coupling piloting members (), wherein saturation values (SCpsat&#x2212;, SCpsat+, SCcopsat&#x2212;, SCcopsat+) of at least one force saturator () 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 (), 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.

Method and device for coupling piloting members

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:

Process and device for controlling an operating lever of a vehicle

A device for combining force between two control units includes force feedback, each control unit including a control stick () and at least one force sensor () 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.

Device for combining force among control units, control unit and aircraft

A piloting device () for piloting a vehicle, in particular an aircraft, has a frame (), a cradle () pivoting with respect to the frame on a first pivot axis (R), a piloting member, called a stick (), pivoting with respect to the cradle () on a second axis (T) orthogonal to and intersecting the first axis, first return elements () for returning the cradle to a predetermined position with respect to the frame, called the neutral position of the cradle, second return elements () 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 (), is arranged between the stick and the frame.

Piloting device for piloting a vehicle, in particular an aircraft

A piloting device for piloting an aircraft includes a piloting member (), a mechanism () for mounting and guiding in rotation the piloting member about at least one rotation axis with respect to a frame (), stops () arranged so as to cooperate with bearing surfaces () integral with the piloting member upstream of the mechanism in order to limit the rotation amplitude thereof, and at least one force sensor (), these being arranged with respect to one another so that each contact of a bearing surface () with a stop () 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.

Piloting device for piloting an aircraft having a protected force sensor

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 (to) for cross-monitoring, for digital processing of signals delivered by sensors () 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.

Electronic operational control device for a piloting member with cross-monitoring, piloting device and aircraft

The invention relates to a piloting device comprising a piloting component () which is connected to at least one steering component (), at least one force sensor () which measures the forces imparted into the kinematic chain () by said piloting component (), a logic circuit () 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 () 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.

Device for piloting a vehicle and method for the motorised assistance and control of such a piloting device

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.

Device for piloting a craft having an electromagnetic actuator

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:

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Figeac, France

Cedric Antraygue