Abstract: An aircraft undercarriage including electrical equipment (2, 3) fastened to a portion (1) of the undercarriage and a lightning protection device (10) comprising at least one shield fastened to said portion (1) of the undercarriage by fastener means so as to extend in register with the electrical equipment (2, 3) in a position that is spaced apart therefrom, the shield comprising at least a first plate (11) made of electrically conductive material that is arranged to absorb a major portion of the heat energy that is generated by the passage of a lightning wave and to discharge the electric charge of the lightning wave. An aircraft fitted with such an undercarriage.

Abstract: An aircraft undercarriage includes a steerable bottom portion carrying one or more wheels and fitted with a steering device configured to turn the steerable bottom portion in response to a steering order. The steering device has a single electromechanical steering actuator having a steering electric motor driving, by a reduction gearing, an outlet pinion on an axis of the steering electric motor. The outlet pinion cooperates with a spur gear secured to the steerable bottom portion. A connection between the steering electric motor and the steerable bottom portion is reversible. The electromechanical steering actuator is fitted with a monitor configured to monitor at least one operating parameter of the steering device and to detect an actuator performance deterioration condition.

Abstract: An aircraft undercarriage carrying at least two wheels (4) and for mounting on an aircraft structure to be movable between a deployed position and a retracted position, the undercarriage being characterized in that the wheels are rotatably mounted on axles (3) carried by arms (2) hinged to a bottom portion of a strut-leg (1) of the undercarriage, each arm being associated with a shock absorber (5) coupled firstly to the arm and secondly to a collar (6) that extends around the strut-leg and that is mounted to slide on the strut-leg between a high position in which the collar bears against an abutment (7) of the strut-leg when the undercarriage is in the deployed position and a low position into which the collar is taken when the undercarriage is moved from the deployed position to the retracted position, so as to bring the wheels closer together.

Abstract: The invention provides an engagement method for engaging a first gear element with a second gear element, at least the second gear element being mounted to move between a meshing position and a disengaged position by means of an actuator. The engagement method including a step of driving at least one of the gear elements in rotation so as to establish a non-zero difference in speed of rotation between said gear elements, and a step of controlling the actuator to perform the following in succession: moving at least the second gear element towards the meshing position; on detecting contact between the gear elements, stopping the movement of the second gear element; and on detecting an ideal angular position for engaging said gear elements, moving the second gear element as quickly as possible into the meshing position.

Abstract: A bogey undercarriage having at least two axles, each carrying at least two wheels, wherein at least one of the axles carries a wheel fitted with a rotary drive device and no brake device, while the other wheels are provided with brake devices and no movement devices is provided. A braking method applied to such an undercarriage is also provided.

Abstract: Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. The stored electrical energy can also be used as a source of emergency backup power. The distribution of the electrical energy is controlled by a power distribution controller. The electric accumulator may be charged by a power source on an aircraft, or it may be pre-charged by an external power source.

Abstract: A control method for controlling an electrical taxiing system adapted to moving an aircraft while it is taxiing, the method comprising the steps of: generating a ground speed setpoint for the aircraft; transforming the ground speed setpoint into an optimized speed setpoint presenting a curve as a function of time that has a predefined function comprising a plurality of linear portions, each having a slope that is a function of the ground speed setpoint; implementing a regulator loop having the optimized speed setpoint as its setpoint; and generating a command for the electrical taxiing system from an output of the regulator loop.

Abstract: The invention relates to a method of driving an aircraft undercarriage between a deployed position and a retracted position, the undercarriage comprising a leg (2) that is hinged to a structure of the aircraft in order to be movable between those two positions and being stabilized in the deployed position by means of a brace member (10) comprising two limbs (11, 12) that are hinged to each other, one of which is coupled to the leg and the other of which is coupled to the structure of the aircraft, the limbs being brought into an aligned position when the leg is in the deployed position. According to the invention, a rotary actuator (20) is arranged on the aircraft, which actuator comprises first and second cranks (22, 24) that are mounted to turn freely about a common axis of rotation but that have a relative angular position that can be controlled, and that are arranged to stabilize the limbs of the brace member in the substantially aligned position.

Abstract: A retractable landing gear includes a main strut having an upper end that is configured to connect to aircraft primary structure and a lower end configured to connect to an axle or bogie truck. An articulated stay has a distal end configured to connect to the aircraft structure and a proximal end pivotally connected to a cardan pin member. The cardan pin member has a cylindrical portion with a first recessed annular channel. The cardan pin member is retained in the socket by a ring assembly formed by two semi-annular ring members that slidably engages the first recessed channel. The ring assembly defines a second recessed annular channel. A collar is configured to be positioned over the second recessed channel, and to contract upon a change in temperature to lockingly engage the second recessed channel, to secure the split ring assembly in the first recessed channel.

Abstract: An aircraft landing gear comprising an axle (100), a wheel (102) borne by the axle, a stack of discs (104) arranged to impose a braking torque on the wheel in response to a pressure imposed on the stack of discs, at least one electromechanical actuator (106) extending facing the stack of discs in order in a controlled manner to apply the imposed pressure to the stack of discs, and an actuator bearer (107) designed to bear the electromechanical actuator. The electromechanical actuator is fixed to the actuator bearer while at the same time being demountable. The actuator bearer is incorporated into the axle in such a way that the axle and the actuator bearer form a single component. There also is a method of demounting a stack of discs from such a landing gear.

Abstract: An aircraft undercarriage having a leg for mounting to move on an aircraft structure between a deployed position and a retracted position is provided. The undercarriage generally includes a brace member arranged between the structure of the aircraft and the leg in order to stabilize the leg in the deployed position, and a drive actuator for moving the leg from the deployed position to the retracted position. The brace member includes a strut arm having a proximal end that is designed to be hinged on the structure of the aircraft. The arm presents a longitudinal slot extending until the slot reaches a distal end in order to terminate in a bend and having slidably engaged therein a finger that is secured to the leg, the drive actuator being coupled to the strut arm.

Abstract: A method of controlling an aircraft electrical taxiing system, the method comprising the steps of: defining a target value (Ld_nmax) for an electrical parameter; generating a nominal force command (Cmd_nom) for the electrical taxiing system; in parallel with generating the nominal force command (Cmd_nom), using a processing system (2) to produce a maximum command force (Force_max) for the electrical taxiing system so that a real value of the electrical parameter reaches the target value (Ld_nmax), the processing system (2) comprising a regulator loop (4); and generating an optimized force command (Cmd_opt) for the electrical taxiing system equal to the smaller of the nominal force command and the maximum command force.

Abstract: A method of fabricating a low alloy steel ingot, the method including a) melting all or part of an electrode by a vacuum arc remelting method, the electrode, before melting, including iron and carbon, the melted portion of the electrode being collected in a crucible, thus forming a melt pool within the crucible; and b) solidifying the melt pool by heat exchange between the melt pool and a cooling fluid, the heat exchange applied serving to impose a mean solidification speed during step b) that is less than or equal to 45 ?m/s and to obtain an ingot of low alloy steel.

Abstract: A brake rod assembly for an aircraft landing gear. The brake rod assembly includes a support member, a first brake rod having a first pivot point and a second pivot point, and a second brake rod. The support member is coupled to the first pivot point, the second brake rod is coupled to the second pivot point, and the first and second pivot points are longitudinally spaced apart along a first portion of the first brake rod.

Abstract: A pressure regulation servo-valve comprising a body having a utilization port, a feed port, and a return port, a spool mounted as a sliding fit in the body, the spool co-operating with the body to define a pilot chamber connected to the utilization port. The spool and the body together further define a priming chamber connected to the feed port via a second constriction and connected to the nozzle via a third constriction, and in which there exists a priming pressure acting on the spool in the first direction.

Abstract: A device for performing anodizing treatment on a part, the device including a treatment chamber including a part for anodizing together with a counter-electrode situated facing the part to be treated, the part to be treated constituting a first wall of the treatment chamber; a generator, a first terminal of the generator being electrically connected to the part to be treated and a second terminal of the generator being electrically connected to the counter-electrode; and a system for storing and circulating an electrolyte, the system including a storage vessel, different from the treatment chamber, for containing the electrolyte; and a circuit for circulating the electrolyte in order to enable the electrolyte to flow between the storage vessel and the treatment chamber.

Abstract: An electrical harness including at least one upstream connector arranged to be electrically connected to a computer, at least one downstream connector arranged to be connected to a complementary connector of an electromechanical actuator, and at least one electric wire electrically connecting the upstream connector and the downstream connector, the electric wire configured such that primary digital control signals produced or transferred by the computer travel over the electric wire via the upstream connector. The electrical harness may also include an electronic unit integrated in the electrical harness, the electronic unit configured to transform the primary digital control signals into analog control signals and to transmit the analog control signals to the electromechanical actuator via the downstream connector.

Abstract: The invention provides a method of moving an aircraft undercarriage comprising a leg (1) that is movable between a deployed position and a retracted position in which the leg is held stationary by means of a strut (2) held in an aligned position by a stabilizer member (4), the method including using a drive actuator (10) for raising the undercarriage from the deployed position to the retracted position. According to the invention, the actuator is coupled firstly to the leg and secondly to the stabilizer member in such a manner that on being activated the actuator begins by causing the stabilizer member to unlock and then moves the undercarriage leg towards the retracted position.

Abstract: A measurement device for measuring speeds of rotation of at least two wheels of an aircraft undercarriage includes a measurement unit and a processor unit associated with each wheel. The measurement unit of each wheel is configured to transform the speed of rotation of the wheel into an electrical magnitude. The processor unit of each wheel is configured to acquire the electrical magnitudes produced by at least two measurement units in order to transform the electrical magnitudes into digital measurement signals representative of the speeds of rotation of at least two wheels, and in order to transmit the digital measurement signals to external equipment.

Abstract: The invention provides a rim for a braked aircraft wheel, the rim comprising an outer circular portion (103) terminated at its ends by flanges (106a, 106b) for receiving a tire, the outer circular portion being connected by a wheel disk (105) to a hub (104) for fitting on an undercarriage axle in order to rotate about an axis of rotation coinciding with a central axis (X) of the rim, the rim being designed to receive a tire on the outside of the outer circular portion and a brake on the inside, on one side of the wheel disk. According to the invention, the outer circular portion (103a) on the side of the wheel disk that is to receive a brake presents, in a plane containing the central axis of the wheel, a profile that has two slopes ?, ? relative to a direction parallel to the central axis on going from the wheel disk to the corresponding flange, and flaring towards the flange.