An improved serviceability gearing element generally includes a support having a plurality of obstacles for co-operating with teeth of a neighboring gearing element. The gearing element further includes a pin, a roller mounted to move in rotation about the pin via a rotary guide, blocking bearings shaped substantially to prevent the roller from moving in translation along the pin, and one or more fasteners for fastening at least one of the blocking bearings to the support.

An aircraft landing gear is disclosed having a first oleo strut include a sleeve portion and a slider portion, the slider portion being slidable within a hydraulic fluid chamber of the sleeve portion, and a second, similar oleo strut. The landing gear also includes a hydraulic fluid balancer having a balance chamber separated into first and second end sections, wherein the hydraulic fluid chamber of the sleeve portion of the first oleo strut is fluidly connected to the first section of the balance chamber and the hydraulic fluid chamber of the sleeve portion of the second oleo strut is fluidly connected to the second section of the balance chamber of the hydraulic fluid balancer.

The invention provides a method of electrically powering an electromechanical braking actuator (1) fitted to an aircraft wheel brake, in which the power supply current (I) delivered to the electromechanical braking actuator is saturated to a saturation value (Isat) in order to limit the current consumed by the electromechanical braking actuator and thereby limit the forces developed by the actuator. The method includes the step of determining the saturation value (Isat) as a function of an internal temperature (T) of the electromechanical braking actuator while it is in operation.

An aircraft includes a first landing gear assembly, a second landing gear assembly, a braking circuit, a brake control circuit, and a braking capability circuit. The landing gear assemblies each include a first braking wheel and a second braking wheel. The braking circuit may apply brakes independently to each of the braking wheels. The brake control circuit actuates braking of the first braking wheels in response to initial receipt of a braking command in a first braking phase and restrict braking at the second braking wheels during the first braking phase until the first braking wheels reach an anti-skid limit at an end of the first braking phase. The braking capability circuit determines a braking capability of the aircraft based on an amount of braking applied to reach the anti-skid limit at the first braking wheels.

A drone docking ports (DDP) mounted on a pole top in close proximity to an accident scene with an openable and closable enclosure, a docking plate having integrated battery wired or wireless recharging pads, and a control module (CM) is disclosed. The CM is adapted to autonomously control all functions of the DDP including actuation of the enclosure and relay of video, audio, and flight control information between the CM and a central monitoring center and/or emergency personnel. A drone with a top and bottom profile design allowing numerous drones to be stacked upon one another and store in the DDP. When the DDP enclosure is in an open position, a drone or stack of drones may initiate a flight from the DDP and to re-dock the drone or stack of drones when the flight is completed, the enclosure may be closed to protect the drone or stack of drones.

The invention provides a drive system for rotating a wheel of an aircraft landing gear. The drive system includes a motor operable to rotate a drive pinion, and a driven gear adapted to be mounted to the wheel. The drive system has a first configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear and a second configuration in which the drive pinion is not capable of meshing with the driven gear. The drive system includes a linear positioning actuator for moving the drive pinion relative to the driven gear. The positioning actuator has a first end and a second end, the first end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the driven gear, and the second end having a pivotal connection with a pivot axis spaced at a fixed distance from an axis of rotation of the drive pinion.

A device for the decontamination of materiel, notably an aircraft such as a military helicopter, using a nuclear, biological and/or chemical decontaminant. The device includes a protective cover that can be adapted to the shape of the materiel, able to form a fluid tight decontamination tunnel around the materiel; at least one decontamination module able to eliminate the contamination from the materiel arranged inside the tunnel formed by the protective cover; an air-blowing module able to be arranged at the entrance to the tunnel formed by the protective cover in order to dispatch air into the said tunnel; and a filtration module able to be positioned at the exit from the tunnel formed by the protective cover in order to destroy contaminated air vapours and/or to recover the decontaminant at the exit from the said tunnel.

A gear element includes a support (3) on which first rollers (10a) and second rollers (10b), which are intended for engaging with the teeth of a neighboring gear element (2), are alternately mounted. Each roller (10a, 10b) is mounted for rotation about its longitudinal axis (X′) via rotary guide means (20) cooperating with end portions of the rollers (10a, 10b). The rotary guide means (20) of the first rollers (10a) and the rotary guide means (20) of the second rollers (10b) are staggered in the vicinity of an outer periphery of the support (3).

A vehicle wheel includes a rim having mounted thereon an inflation valve and a tire. The inflation valve is extended by an inflation channel extending through the rim and opening out into a volume of gas defined by the rim and the tire. The inflation valve is arranged in the vicinity of a flange of the rim.

Methods and associated systems for autonomous package delivery utilize a UAS/UAV, an infrared positioning senor, and a docking station integrated with a package delivery vehicle. The UAS/UAV accepts a package for delivery from the docking station on the delivery vehicle and uploads the delivery destination. The UAS/UAV autonomously launches from its docked position on the delivery vehicle. The UAS/UAV autonomously flies to the delivery destination by means of GPS navigation. The UAS/UAV is guided in final delivery by means of a human supervised live video feed from the UAS/UAV. The UAS/UAV is assisted in the descent and delivery of the parcel by precision sensors and if necessary by means of remote human control. The UAS/UAV autonomously returns to the delivery vehicle by means of GPS navigation and precision sensors. The UAS/UAV autonomously docks with the delivery vehicle for recharging and preparation for the next delivery sequence.