Abstract: Various shaped abrasive particles are disclosed. Each shaped abrasive particle includes a body having at least one major surface and a side surface extending from the major surface.

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 method for engaging a first gear element with a second gear element is provided. The second gear element is mounted to be mobile between a meshing position and a position of disengagement using an actuator. The method includes driving one or more of the first and second gear elements in rotation to form a non-zero rotation speed difference between the first and second gear elements and controlling the actuator to successively displace the second gear element to the meshing position, and when an intermediate position of the second gear element is detected, stop the displacement of the second gear element, and when an angular position of engagement of the first and second gear elements is detected, displace the second gear element to the meshing position.

Abstract: A spearing end effector for a robotic spearing device capturing and sorting a selected item from a mass of items and having a robotic manipulator with the spearing end effector mounted at an end thereof. The robotic spearing device comprises: a spearing end effector body; a spike; a linear actuator having the spike mounted thereon; and a propeller. The spike is configurable between a retracted configuration where it is entirely located inside the spearing end effector body and an extended configuration where it extends outwardly from therefrom. The spike is engageable to the selected item when configured in the extended configuration. The linear actuator is movable to configure the spike between the retracted configuration and the extended configuration. The propeller is selectively activatable to propel the selected item in a propelling direction during an ejection of the selected item from the spearing end effector.

Abstract: A pressure measuring probe, in particular for use in an aircraft is disclosed. In one aspect, the pressure measuring probe includes at least one acquisition tube, including a capability for discharging water and captured crystals contained in the atmosphere, where the discharge capability includes a drainage hole arranged in a rear partition of the tube, in the axis of symmetry thereof and in the flow direction of the flow of air.

Abstract: The invention relates to a method of determining at least one quantity relative to the adsorption of at least one adsorbable gas in a sample of a porous medium, wherein the following steps are carried out: (i) determining a Darcy velocity by injecting an inert gas for a given gradient and by measuring the inert gas flow rate downstream from the sample, (ii) determining an adsorbable gas breakthrough velocity by injecting the adsorbable gas for the same gradient and by measuring the adsorbable gas quantity downstream from the sample as a function of time, and (iii) determining a kinematic porosity using the ratio of the Darcy velocity to the adsorbable gas breakthrough velocity.

Abstract: The invention relates to a phase-change material reservoir 9 for a heat exchanger of an air-conditioning installation of a vehicle, the reservoir 9 being arranged between two reservoir plates 10a, 10b and having filling means 14, characterized in that the filling means 14 include at least one tube 15 delimiting a filling channel 19 arranged outside the reservoir 9 against a first plate 10a of the reservoir 9.

Abstract: Drive equipment for rotating by friction an aircraft wheel equipped with a drive track and mounted to turn about an axis (X) on an axle of an aircraft undercarriage. The equipment comprise a base (22), a slide (24) mounted on the base on a sliding axis extending in a radial direction (R1, R1), a support (26) pivotable on the slide on an axis parallel to the rotation axis of the wheel; two rollers (21) rotatable on rotation axes parallel to the pivot axis; a central shaft (28) mounted for rotation on the support and being in engagement with the two rollers to provide their rotation; and an actuator (23A, 23B, 30) for moving the slide and the support between a disengagement position with the rollers distant from the wheel drive track and an engagement position with the rollers are held in contact with the drive track of the wheel.

Abstract: An assembly for rotationally friction driving the wheel of an airplane provided with a driving track. The assembly has a base intended to be fixed to a lower part of the landing gear, two arms mounted to pivot on the base, and rollers so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving the roller. A central pinion is mounted so as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion. A drive actuator acts on the arms of the assembly so as to position the assembly either in a disengaged position in which the rollers are separated from the driving track, or in an engaged position in which the rollers are held to rest on the driving track.

Abstract: The invention relates to a method for engaging a first gear element with a second gear element, at least the second gear element being mounted to be mobile between a meshing position and a position of disengagement using an actuator. The method comprises the step of driving at least one of the gear elements in rotation to form a non-zero rotation speed difference between said gear elements and the step of controlling the actuator to successively: displace at least the second gear element to the meshing position, when an intermediate position of the second gear element is detected, stop the displacement of the second gear element, when an angular position of engagement of said gear elements is detected, displace the second gear element to the meshing position.

Abstract: Gaming systems and methods for integrated computer-related and physical game play interactions between a game player, a physical game piece character and an electronic device are defined. The physical game piece character may be a combination of smaller parts where each combination transmits a unique alphanumeric identifier and control signals to an electronic device game application, where the game application features the physical game piece character and is responsive to the signals from the physical game piece character and transmits control signals to the physical game piece, which responds with sensory signals.

Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.

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 method for fixing to an aircraft landing gear (1) at least one actuator (30) for rotatably driving a wheel (3) which is rotatably mounted on an axle (2) of the landing gear, the wheel being associated with a brake (5). The brake has an actuator carrier (8) which carries brake actuators, the actuator carrier being fitted onto the axle and stopped in terms of rotation by an obstacle (12) which is fixedly joined to the landing gear and which is introduced into one of several stop holes (11) of the actuator carrier. The drive actuator is fixedly joined to the actuator carrier in the region of a stop hole of the actuator carrier which does not receive the obstacle.

Abstract: An electrical voltage-generating piezoelectric device comprising at least a first blade (1) with a curved portion (10) defining a first arm (11) and a second arm (12) of the blade, the first arm (11) being intended to be fastened to a fixed support, the second arm (12) being substantially flat and having a free end (120) designed to oscillate around its resting position under the effect of mechanical force, at least one piezoelectric element (31) resting upon one of the main surfaces (14) of the second arm (12) of the first blade. The device also includes a second blade (2) identical in structure to the first blade (1), the first arms (11, 21) of the first and second blades (1, 2) being fastened together on all or part of their surfaces and being fixed relative to each other.

Abstract: A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.

Abstract: The invention relates to a phase-change material reservoir 9 for a heat exchanger of an air-conditioning installation of a vehicle, the reservoir 9 being arranged between two reservoir plates 10a, 10b and having filling means 14, characterized in that the filling means 14 include at least one tube 15 delimiting a filling channel 19 arranged outside the reservoir 9against a first plate 10a of the reservoir 9.

Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) including a part intended to be arranged at a skin (27) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator (14) associated with functional elements (25a) of the aircraft forming a heat source giving off heat during their operation and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

Abstract: A pressure measuring probe, in particular for use in an aircraft is disclosed. In one aspect, the pressure measuring probe includes at least one acquisition tube, including a capability for discharging water and captured crystals contained in the atmosphere, where the discharge capability includes a drainage hole arranged in a rear partition of the tube, in the axis of symmetry thereof and in the flow direction of the flow of air.

Abstract: A lithium-ion accumulator successively includes a first current collector; a negative electrode in contact with the first current collector; an electrode separator comprising an electrolyte, in contact with the negative electrode; a positive electrode in contact with the electrode separator; and a second current collector in contact with the positive electrode. The second current collector is made of aluminum covalently grafted with at least one phenyl aromatic group C6(Ri)5, in which formula: Ri designates R1, R2, R3, R4 and R5 which are independently from one another selected from the group including: C(?O)O—Y+; SO3?Y+; CH2—SO3?Y+; NR3+X?; OH; PO3H?Y+; H; F; CnF2n+1; CnH2n+1; NO2; —O—CH2—O—; imidazole groups; and derivatives of imidazole groups; with Y?H, Na, K, Li, NR?4; X?F, Cl, Br, I; n being an integer in the range from 1 to 10; R?CmH2m+1; R??H, CmH2m+1 and mixtures thereof, m being an integer in the range from 1 to 10; at least two groups Ri being different from H.