Abstract: A shock absorber includes a housing and an end wall slidably disposed within the housing. The end wall and the housing cooperate to define at least a portion of a cavity within the housing. The cavity is filled with a fluid, and a piston is slidably disposed within the cavity. Movement of the piston within the cavity compresses the fluid to provide a spring force. The shock absorber further includes a compensator coupled to the end wall. The compensator positions the end wall within the housing to change a volume of the cavity in response to a change in a temperature of a first element of the compensator.

Abstract: A landing gear system includes a drive shaft extending through an axle. A wheel with a drive surface is rotatably coupled to the axle. A drive assembly, which has disengaged and engaged states, includes a drive element and an idler element. The drive element, which has an engagement feature, is coupled to the drive shaft for rotation about an axis. The engagement feature has first and second diameters when the drive assembly is in the disengaged and engaged states, respectively. The idler element is frictionally engaged with the engagement feature of the drive element to transfer rotation of the drive element to the wheel when the drive assembly is in the engaged state. The idler element is disengaged from at least one of the engagement feature of drive element and the wheel when the drive assembly is in the disengaged state.

Abstract: A landing gear system includes wheel rotatably coupled to an axle. A driveshaft extends through a cavity formed in the axle and is rotatable about an axis. A planetary gear includes a sun gear operably coupled to the drive shaft and a planet gear operably engaging the sun gear. The planetary gear further includes a ring gear that surrounds and is operably coupled to the planet gear so that rotation of the drive shaft rotates the ring gear. A clutch assembly is selectively moveable between an engaged state and a disengaged state. The clutch assembly transfers rotation of the ring gear to the wheel when the clutch assembly is in the engaged state, and the clutch assembly does not transfer rotation of the wheel to the ring gear when the clutch assembly is in the disengaged state.

Abstract: A truck beam for an aircraft landing gear assembly is provided. The truck beam includes an elongate hub having first and second ends. The hub is rotatably mountable to a shock strut of the landing gear assembly. A first leg extends radially in a first direction from the first end of the hub. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side about a first wheel axis. A second leg extends radially in a second direction from the second end of the hub and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.

Abstract: An aircraft brake system comprising: a first group of at least one electromechanical actuator, a second group of at least one electromechanical actuator, a first control device with a first software module and a second software module, the second software module being configured to control the first group of at least one actuator at least in the event of a fault of the first software module, a second control device with a third software module and a fourth software module, the fourth software module being configured to control the second group of at least one actuator at least in the event of a fault of the third software module, wherein the first device module and the second control device are dissimilar. The invention also relates to an aircraft equipped with this system.

Abstract: A torque link assembly for a landing gear includes a lower torque link and an upper torque link that releasably engage first and second quick release pin assemblies. The pin assemblies each include a housing attached to one of the torque links, and a locking pin member extending through the housing. The locking pin member includes a rod portion and a pin portion, and is slidable between an engaged position and a disengaged position for hingedly connecting/disconnecting the torque links. One of the housing and the locking pin member includes a channel having a longitudinal portion and a circumferential portion, and the other has a guide pin that engages the channel. The guide pin is in the longitudinal portion of the channel when moving between the engaged and disengaged positions, and is retained in the disengaged position when the guide pin is in the circumferential portion of the channel.

Abstract: A shock absorber includes a housing and an end wall slidably disposed within the housing. The end wall and the housing cooperate to define at least a portion of a cavity within the housing. The cavity is filled with a fluid, and a piston is slidably disposed within the cavity. Movement of the piston within the cavity compresses the fluid to provide a spring force. The shock absorber further includes a compensator coupled to the end wall. The compensator positions the end wall within the housing to change a volume of the cavity in response to a change in a temperature of a first element of the compensator.

Abstract: A method of additive manufacturing including defining contiguous portions over a ceiling of a cavity of a part, including a central portion defined entirely by first edges, and peripheral portions defined by second edges and by a portion of a frontier of the ceiling. Defining a capital by facets that bear against the first edges and that converge towards an apex, and defining a slender support that extends from the capital to a cavity floor while being centered on the apex. For each peripheral portion, defining a capital by facets that bear against the second edges and that converge towards a terminal edge extending in a plane that is normal to a wall of the cavity, and defining a rib support that extends in the normal plane between the terminal edge and a wall of the cavity. Manufacturing the part including the cavity while making the supports and capitals.

Abstract: The invention relates to a method for controlling the torque of a drive device (1) for rotating wheels (2) of an aircraft comprising actuators for selectively driving rotating wheels of the aircraft to ensure its movement on the ground, comprising the step of regulating a torque generated by the drive device according to a torque setpoint (4) issued by the pilot. According to the invention, the method involves the step of generating, as long as the torque setpoint is not sufficient to guarantee a stable movement speed of the aircraft, a replacement torque setpoint (5) to allow the aircraft to move at a stable speed, and substituting the replacement torque setpoint for the torque setpoint generated by the pilot.

Abstract: A method of determining a service interval for an actuator of a landing gear assembly is suitable for used with a landing gear assembly in which the actuator positions the landing gear assembly between a stowed position and a deployed position. The method includes the steps of determining an actuator travel value for a time interval and increasing a total actuator accumulated travel value by the actuator travel value for the time interval. The method further includes the step of comparing the total actuator accumulated travel value to a predetermined value.

Abstract: Techniques and methodologies for servicing a shock strut are provided that account for the variability in gas solubility of the shock strut while in-service. These examples incorporates knowledge of the shock strut's stoke history in order to estimate/predict the amount of gas in solution, its percentage saturation, etc. This may permit a more refined knowledge of the true servicing state of the shock strut.

Abstract: An aircraft undercarriage including a wheel, a support, a drive system, a mover system, a first pair of links, and a locking actuator. The drive system drives rotation of the wheel and is mounted to move relative to the support between an engaged position and a disengaged position. The mover system moves the drive system between the engaged and disengaged positions. The first pair of links are hinged to each other about a first hinge axis to pivot during the movement of the drive system between the engaged and disengaged positions. The locking actuator acts on a first target to lock or unlock the drive system. The first target is carried by one of the links.

Abstract: An aircraft wheel rim includes a main portion and a removable portion. The main portion includes a hub and a disk extending between the hub and an annular outer portion that receives a tire and is shaped to form a rim one of its sides of the annular outer portion. A second side of the annular outer portion is shaped to receive the removable portion, which forms a second flange on the second side of the annular outer portion after a tire has been put into place. The rim further includes a blocking device that limits rotation of the removable portion relative to the main portion. The blocking element include at least one key having a head engaged in a matching receptacle in the removable portion and a root engaging a steel peg that is shrink fitted in the main portion.

Abstract: A remote towing interface is used to couple a towbar to an aircraft having a fuselage and a steerable landing gear. The remote towing interface includes a towbar coupler mounted to the aircraft and configured to releasably couple a towbar to the aircraft. The remote towing interface further includes a sensor and a controller. The sensor is configured to sense a position of the towbar relative to the aircraft when the towbar is coupled to the towbar coupler, and the controller controls the steerable landing gear according to the sensed position of the towbar relative to the aircraft.

Abstract: A landing gear for a vehicle includes a strut configured for reciprocating movement between a stowed position and a deployed position. A shock absorber has a first element slidingly disposed within the strut and a second element slidingly coupled to the first element. A trailing arm is rotatably coupled to the second element. A first linkage is coupled to the first element, wherein the first linkage drives the first element between a raised position when the strut is in the stowed position and a lowered position when the strut is in the deployed position. The landing gear further includes a second linkage coupled to the trailing arm. The second linkage rotates the trailing arm between a first trailing arm position when the strut is in the stowed position and a second trailing arm position when the strut is in the deployed position.

Abstract: A machine for forming an annular textile preform includes: a horizontal sheet-forming turntable for forming a helical fiber; a horizontal intermediate turntable positioned under the sheet-forming turntable; a horizontal intermediate unwinder positioned on the intermediate; a final horizontal unwinder positioned under the intermediate unwinder; and a horizontal preform-forming turntable positioned under the final unwinder.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.

Abstract: The invention relates to a hydraulic actuator comprising a cylinder (1) in which a piston (2) secured to a rod (4) is mounted so as to slide in a sealed manner in order to delimit in the cylinder a hydraulic extension chamber (5) and a hydraulic retraction chamber (6) that are connected to respective ports, the hydraulic actuator comprising means for slowing the piston when the piston approaches a retracted position. According to the invention, the slowing means comprise first and second hydraulic lines (7, 8) extending between the extension port and the extension chamber, the first hydraulic line comprising a seat (13) while the piston bears a retractable finger (10) having an end (14) that comes to bear against the seat in order to close the first hydraulic line (7) when the piston approaches the retracted position, such that only the second hydraulic line (8) remains open while the piston completes its travel towards the retracted position. Landing gear and aircraft comprising such an actuator.

Abstract: A braking system architecture for aircraft, the architecture comprising: a brake including friction members and electromechanical actuators for exerting a braking torque on the wheel; a computer situated in the fuselage of the aircraft and arranged to produce first control signals; and a junction box situated on the undercarriage, the junction box being connected to the computer and to the electromechanical actuators, the junction box being configured to receive the first control signals and to use the first control signals to produce second control signals for application to the electromechanical actuators in order to control the electromechanical actuators.