The invention relates to an aqueous composition for the electrolytic deposition of a chromium coating on the surface of a substrate, which has a pH of between 0 and 1 and which contains a trivalent chromium salt, glycine, an alkali metal salt, an aluminium salt and, optionally, an ammonium salt. The chromium plating process according to the invention comprises the immersion of the substrate to be treated in this composition and the application of a current between this substrate and an anode. This process makes it possible to form a high-quality chromium coating on the entire surface of the substrate.
The invention relates to a device (1) for encoding information between a plurality of normally closed switches (P1 . . . Pn) arranged on an operating lever (2) and a control device (9), said switches being connected in series between a voltage line (3) and a measuring line (5), each switch (Pi) being associated with a single resistor (Ri) connected between the terminal of the switch closest to a voltage source (Vcc) and the measuring line. The encoding device thus allows a hierarchy of the switches to be obtained.
B64C 27/56 - Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
H03M 1/76 - Simultaneous conversion using switching tree
H03M 1/78 - Simultaneous conversion using ladder network
3.
Process and device for manufacturing a composite part enabling the evacuation of gas from the composite part
Disclosed is a process for manufacturing a part, named composite part, formed from at least one composite material including at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, wherein: a composite blank of the composite part is prepared; and a step of curing the polymer matrix of the composite blank is carried out, exerting a pressure on at least one pressed face of the composite blank. The pressure is exerted in the form of a pressure gradient applied to the pressed face of the composite blank so as to cause the gas present within the composite part to flow from a zone of maximum pressurization to a gas evacuation zone. Also disclosed is a device for manufacturing such a part.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
The invention relates to a device (1) for encoding information between a plurality of normally closed switches (P1...Pn) arranged on an operating lever (2) and a control device (9), said switches being connected in series between a voltage line (3) and a measuring line (5), each switch (Pi) being paired with a single resistor (Ri) connected between the switch terminal closest to a voltage source (Vcc) and the measuring line. The encoding device thus makes it possible to obtain a hierarchy of switches.
The invention relates to a process for manufacturing a part, referred to as a composite part, formed from at least one composite material comprising at least one layer of a reinforcing structure impregnated with a polymer matrix within which the reinforcing structure extends, in which: - a composite blank (1) of said composite part is prepared, - a step of curing the polymer matrix of said composite blank is carried out, while exerting pressure on at least one pressed face (2) of said composite blank, characterized in that said pressure is exerted, in the form of a pressure gradient, applied to said pressed face of said composite blank, so as to make the gas present within the composite part flow from a zone of maximum pressurization to a gas evacuation zone (4). The invention also relates to a device for manufacturing such a part.
B29C 70/44 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
A de-icing device is provided for at least one surface portion of a rotor blade liable to be covered with a layer of ice. The device includes: at least one first heating device adapted to permit detachment of at least part of the layer of ice, as well as at least one second heating device including heating elements extending facing only part of the surface portion so as to circumscribe at that location closed-contour zones of the surface portion. The heating elements of the second heating device are adapted to cause breaking of the ice through the thickness of the layer of ice, and the first heating device extends at least partly facing the inside of the closed-contour zones.
An actuator of an aircraft includes at least one limit stop in which at least one of the bearing surfaces, named destructible bearing surface (19), has at least one destructible portion which is able to, and is arranged to, be irreversibly deformed under the effect of the co-operation by limit contact between the driving member bearing surface (19) and the driven member bearing surface (20). Each destructible portion of each destructible bearing surface is mounted to be removable with respect to the stop as to be able to be replaced.
A bearing for guiding a first guided piece includes a first bearing surface with respect to a second bearing surface fixedly attached to a second guided piece. At least one first intermediate piece is interposed between the first bearing surface and the first guided piece and at least one first automatic release assembly for i) in a first assembly state, fixedly attaching the at least one first intermediate piece and the first guided piece for guidance forces which are lower than a triggering value, and ii) in a release state, permitting a relative displacement of the first guided piece with respect to the at least one first intermediate piece, at least in one displacement orientation, for guidance forces which are greater than the triggering value of the first assembly.
F16C 29/00 - Bearings for parts moving only linearly
F16F 9/20 - Devices with one or more members, e.g. pistons, vanes, moving to and fro in chambers and using throttling effect involving only straight-line movement of the effective parts with a closed cylinder and a piston separating two or more working spaces therein with the piston-rod extending through both ends of the cylinder
A device for supplying electricity to at least one secondary electric load (30) on-board a turbomachine rotor (12) including a main circuit for transmitting main electric power to at least one main on-board electrical load (16), includes a device (15) for rotatably and electrically connecting the stator and the rotor, and at least one secondary circuit for transmitting a secondary electric power including at least one secondary conductor (28) of the stator connected to a secondary electric power source (29) suitable for outputting a secondary power in the form of a power signal with a secondary frequency selected such as to enable selective, interference-free transmission of the secondary power via the rotary electric connection device (15), separately from the main power transmission.
H02J 3/02 - Circuit arrangements for ac mains or ac distribution networks using a single network for simultaneous distribution of power at different frequenciesCircuit arrangements for ac mains or ac distribution networks using a single network for simultaneous distribution of ac power and of dc power
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.
A device and a control method are described for a swinging aircraft door (3), mobile around a swinging axis (21) substantially parallel to the longitudinal axis of the aircraft via a motorized mechanism and having integrated boarding stairs (31). The method includes the capture of electromagnetic or ultrasonic radiation using at least one sensor (401, 501); the detection of something on the stairs on the basis of captured electromagnetic or ultrasonic radiation, in order to deduce therefrom whether a detection condition is satisfied or not; and, driving of the motorized mechanism in order to control the closure of the door in response to a closure command except in case of detection of something on the stairway.
an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurized gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
A blade includes an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (23). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion (21) to pass through. The base of the aerodynamic portion (21) has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion (21) in the blade shank (20).
A device for opening and closing according to the invention relates to an aircraft door (2) hinged around an axis (6) substantially parallel to the longitudinal axis the aircraft comprising a motorized mechanism and a driving system combined with a control device comprising a system for acquisition of the angular position of the door (2) relative to the structure (4) the aircraft, where said angular position acquisition system for the door comprises at least one inclinometer (20) combined with the door (2).
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.
B64D 31/06 - Initiating means actuated automatically
H02P 6/00 - Arrangements for controlling synchronous motors or other dynamo-electric motors using electronic commutation dependent on the rotor positionElectronic commutators therefor
G05B 1/01 - Comparing elements, i.e. elements for effecting comparison directly or indirectly between a desired value and existing or anticipated values electric
G05B 11/42 - Automatic controllers electric with provision for obtaining particular characteristics, e.g. proportional, integral, differential for obtaining a characteristic which is both proportional and time-dependent, e.g. P. I., P. I. D.
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.
A propeller blade includes an aerodynamic portion and a blade shank, a hub assembly (28, 32) which provides anchoring in a hub, a blade shank assembly of the aerodynamic portion, a safety device including a safety element (24) which extends from a distal assembly in the aerodynamic portion to a proximal assembly (26, 27) in the blade shank and which is adapted to be able to anchor the aerodynamic portion in the blade shank, wherein the blade shank assembly is anchored radially outside the hub assembly, the proximal assembly is anchored to the blade shank radially inside the hub assembly, and the distal assembly and/or the proximal assembly has a strictly positive radial clearance (30).
F01D 21/04 - Shutting-down of machines or engines, e.g. in emergencyRegulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator, e.g. indicating such position
The invention relates to a device for supplying electricity to at least one secondary electric load (30) on-board a turbine engine rotor (12) including a main circuit for transmitting main electric power to at least one main on-board electrical load (16), comprising a device (15) for rotatably and electrically connecting the stator and the rotor, and at least one secondary circuit for transmitting a secondary electric power including at least one secondary conductor (28) of the stator connected to a secondary electric power source (29) suitable for outputting a secondary power in the form of a power signal with a secondary frequency selected such as to enable selective, interference-free transmission of the secondary power via the rotary electric connection device (15), separately from the main power transmission.
H02J 3/34 - Arrangements for transfer of electric power between networks of substantially different frequency
H02J 3/02 - Circuit arrangements for ac mains or ac distribution networks using a single network for simultaneous distribution of power at different frequenciesCircuit arrangements for ac mains or ac distribution networks using a single network for simultaneous distribution of ac power and of dc power
20.
Motorized device for opening and/or closing an aircraft door
A device for opening or closing an aircraft door includes an electric motor; a connector to connect the motor, and a driver. The driver includes a screw and nut system having a screw rotationally driven by the motor. The driver is configured to drive continuously and in sequence the connector with the door in a translational movement along one preset direction and then in rotational movement.
Rotary-shaft brake system includes a rotary braking member attached to a rotary shaft, first and second friction members arranged on either side of the rotary braking member, each friction member being moveable between a first braking position when the friction members are in contact with the rotary braking member and a second idle position away from the rotary braking member, a bracket holding the friction members and guiding device and control device controlling movement of the friction members on the bracket. The control device comprises a linear actuator acting on at least a first lever and a solid elastically deformable element.
F16D 55/22 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads
F16D 55/224 - Brakes with substantially-radial braking surfaces pressed together in axial direction, e.g. disc brakes with axially-movable discs or pads pressed against axially-located rotating members by clamping an axially-located rotating disc between movable braking members, e.g. movable brake discs or brake pads with a common actuating member for the braking members
F16D 66/00 - Arrangements for monitoring working conditions of brakes, e.g. wear or temperature
The present invention relates to a device which comprises: a tubular body (2) and a first attachment means (6), a piston (30) provided with a rod (12) connected to a second attachment means (10), the piston (30) sliding inside the tubular body (2) and defining inside said body a working chamber filled with hydraulic fluid, an accumulator comprising a rigid shell (20) inside of which a separation means (40) is located, defining a compensation chamber (42) that is filled with hydraulic fluid and is in communication with the working chamber, and a chamber (47) filled with pressurised gas, the rigid shell (20) being a metal shell produced by means of welded assembly and the accumulator being made such as to obtain an entirely welded enclosure (47) containing the gas.
F16F 9/06 - Springs, vibration-dampers, shock-absorbers, or similarly-constructed movement-dampers using a fluid or the equivalent as damping medium using both gas and liquid
F15B 1/10 - Accumulators using a gas cushionGas charging devicesIndicators or floats therefor with flexible separating means
B64C 1/14 - WindowsDoorsHatch covers or access panelsSurrounding frame structuresCanopiesWindscreens
23.
DEVICE FOR COMBINING FORCE AMONG CONTROL UNITS, CONTROL UNIT AND AIRCRAFT
The invention relates to a device for combining force between two control units that comprises force feedback, each control unit comprising 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 said force feedback value (Fcor_p) according to at least one parameter taken from the absolute value of the control force (Fcp) of said second control unit and the difference between the control force values of each control unit. The invention extends to a control unit comprising such a device for combining forces as well as to an aircraft provided with such control units.
G05G 5/03 - Means for enhancing the operator's awareness of the arrival of the controlling member at a command or datum positionProviding feel, e.g. means for creating a counterforce
G05G 11/00 - Manually-actuated control mechanisms provided with two or more controlling members co-operating with one single controlled member
24.
Piloting device for piloting a vehicle, in particular an aircraft
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.
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
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.
G05G 5/04 - Stops for limiting movement of members, e.g. adjustable stop
G05G 9/047 - Manually-actuated control mechanisms provided with one single controlling member co-operating with two or more controlled members, e.g. selectively, simultaneously the controlling member being movable in different independent ways, movement in each individual way actuating one controlled member only in which movement in two or more ways can occur simultaneously the controlling member being movable by hand about orthogonal axes, e.g. joysticks
26.
Propeller blade with reinforcing spars and boxes, and propeller comprising at least one such blade
b) in surface contact with the hollow casing (1) so as to provide structural support for the hollow casing (1), and at least two cavities (15, 16) which are spaced apart in the direction of the chord (25), wherein the propeller blade further comprises at least two reinforcing spars (6, 7) which extend between the framework and the hollow casing.
means for guiding the opening of the gate-valve via the pressurized fluid located in the chamber when the door is in the opening position, so as to open the exhaust pipe in order to set said chamber of the cylinder to atmospheric pressure in a rapid manner once the door is open.
F15B 11/048 - Systems essentially incorporating special features for controlling the speed or the actuating force or speed of an output member for controlling the speed depending on the position of the working member with deceleration control
28.
Aircraft hatch emergency opening actuator including opening delay means
an active position, in which the fluid means are injected at the point of the fluid circuit, means for delaying the injection of the fluid means into the cylinder including a mobile element in the fluid circuit, delaying opening of the circuit when the injection means are in the active position, the injection delay being determined by a time of movement of the mobile element.
The present invention relates to devices for damping the movement of a body Co between two positions at the end of travel. The device according to the invention is essentially characterized in that it comprises two abutments B1, B2, a cylinder 10, a wall 11 closing off the end 12 of the cylinder 10, a piston 14 delimiting a chamber 16 with variable volume, a cylinder 20 with an external section at most equal to the internal section of the cylinder 10, a mounting unit for mounting the cylinder 20 in cooperation with the piston 14 so that the latter closes off the end 21 of this cylinder 20, a piston 24 delimiting a chamber 26 with variable volume, a first fluid Li filling the two chambers 16, 26, a communicating unit 30 for communication under pressure loss between the chambers 16, 26, an abutment 40 mounted in cooperation with the piston 24 so that this abutment 40 has a movement correlative with that of the piston 24, and a connecting unit 50 for connecting the cylinder 20 to the body Co. Application notably to the control for opening and closing an aircraft door.
Actuator for gas-operated emergency opening of an openable element of an aircraft, having the ability to vent the gas. The actuator for emergency opening of an openable element of an aircraft includes a thrustor, a pressurised-gas reservoir where the gas reservoir having a membrane capable of being perforated in order to actuate said thrustor, a movable perforator arranged to perforate said membrane of said reservoir in order to release the gas into the thrustor via a first fluid circuit, and a venting circuit that vents, away from the thrustor, the gas contained in the reservoir, in the event of accidental rupture of said membrane, via a second fluid circuit which does not actuate said thrustor.
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.
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 caused by the radial offset are corrected.
G01B 7/30 - Measuring arrangements characterised by the use of electric or magnetic techniques for measuring angles or tapersMeasuring arrangements characterised by the use of electric or magnetic techniques for testing the alignment of axes
33.
Electronic operational control device for a piloting member with cross-monitoring, piloting device and aircraft
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.
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.
patents
