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 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: 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: 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: 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: 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: 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: 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 piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which 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 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 the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment (100), the equipment comprising at least one part intended to be arranged at a skin (27) of the aircraft, and means for fastening on said skin outside the aircraft and means for heating the part, characterized in that the fastening means comprise means in the form of tubular tabs (101, 102), in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with means forming a heat source arranged inside the aircraft 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, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least partially formed in the tubular tabs (101, 102) of the fastening means.

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 heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment (25) includes a part (30, 31) intended to be arranged at the skin (27) 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 (14) and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator (14), 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: A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) outside of the aircraft and heating elements for that part, which 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 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 the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

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: The invention relates to an assembly for rotationally friction driving the wheel of an airplane (3) provided with a driving track (4) and so mounted as to rotate about an axis of rotation on an axle (2) carried by the lower part of an airplane landing gear, with the assembly comprising: a base (22) intended to be fixed to the lower part of the landing gear; two arms (24) mounted to pivot on the base; rollers (21) so mounted as to rotate at the end of each arm, with each roller being associated with a pinion for rotationally driving (31) the roller; a central pinion (26) so mounted as to rotate along the arms pivot axis so that the rollers driving pinions engage with the central pinion; actuating means (29) so acting on the arms of the assembly as to position same 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 with a predetermined bearing force.

Abstract: The invention relates to 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) which comprises 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 the stop holes (11) of the actuator carrier, wherein 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: 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: A probe for measuring the total pressure of an airflow is intended to equip an aircraft and a method of using the probe. The probe comprises a Pitot tube, two separate heating wires supplied separately and allowing each one to heat an external part of the probe, and means of distribution of a given maximum power to each of the two heating wires as a function of the current temperature of each of the two parts. A method consists in giving priority to the reaching of a predefined minimum temperature of a first of the two parts of the probe by allocating to the first part of the probe a predefined share of the given maximum power for as long as the temperature of the first part is below a predefined minimum temperature.