Abstract: An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element. First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.

Abstract: An aircraft undercarriage includes an upper element for connecting to an aircraft structure and a lower element carrying an axle. The lower element is mounted to be movable in translation relative to the upper element along a longitudinal axis, and a shock absorber is arranged to damp movements in translation of the lower element relative to the upper element. First and second portions of a spring are connected respectively to the upper element and to the lower element so that during movement in translation of the lower element relative to the upper element, the spring opposes any turning of the lower element relative to the upper element about said longitudinal axis.

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: 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 relates to a tubular fusible member (21) extending along a longitudinal axis (AL) and for engaging in a two-lug clevis (14) and a single-lug clevis (12) in order to form a hinge (11). According to the invention, the fusible member (21) is constrained in rotation with one of the clevises (12, 14), and it presents a cross-section of shape that varies gradually between a central section and two distal sections, each distal section having reinforced thickness in its regions that extend parallel to the bending plane (PF) in which the fusible member (21) bends when it is stressed, the central section having a second moment of area relative to an axis normal to the bending plane (PF) that is greater than the second moment of area of the distal sections.

Abstract: A display system and method including screens in a cockpit of an aircraft. A control unit is configured to command the display according to a normal display mode, wherein the control unit is configured so as to command the display such that subsequent to the occurrence of an event on board the aircraft leading to the display of an interactive element in an interaction window, the control unit commands the display of the interaction window on one of the screens of the screens at least while an action by an operator is required on the interactive element, and a reconfigured display mode, wherein the control unit is configured to command the display, on a second screen including a signaling area, of a display window that is normally displayed on a first screen in the normal display mode, and to command the display of an indicator in the signaling area if the interaction window is not displayed on a screen of the screens when an action by an operator is required on the interactive element.

Abstract: The invention relates to a tubular fusible member (21) extending along a longitudinal axis (AL) and for engaging in a two-lug clevis (14) and a single-lug clevis (12) in order to form a hinge (11). According to the invention, the fusible member (21) is constrained in rotation with one of the clevises (12, 14), and it presents a cross-section of shape that varies gradually between a central section and two distal sections, each distal section having reinforced thickness in its regions that extend parallel to the bending plane (PF) in which the fusible member (21) bends when it is stressed, the central section having a second moment of area relative to an axis normal to the bending plane (PF) that is greater than the second moment of area of the distal sections.

Abstract: A multivariable model predictive controller (MPC) for controlling a coalbed methane (CBM) production process. The MPC includes input ports for receiving a plurality of measurement signals including measured process parameters from CBM wells in a well field. A control loop includes a mathematical model that controls the CBM gas production. The model includes individual production characteristics for each CBM well that predicts its behavior for controlled variables (CVs) with respect to changes in manipulated variables (MVs) and disturbance variables (DVs). The control loop calculates future set points for the MVs based on the model and the measured process parameters for CBM production to achieve at least one control objective for the well field. A plurality of output ports provide control signals for implementing the future set points which when coupled to physical process equipment at the plurality of CBM wells control the physical equipment to reach the future set points.

Abstract: A multivariable model predictive controller (MPC) for controlling a coalbed methane (CBM) production process. The MPC includes input ports for receiving a plurality of measurement signals including measured process parameters from CBM wells in a well field. A control loop includes a mathematical model that controls the CBM gas production. The model includes individual production characteristics for each CBM well that predicts its behavior for controlled variables (CVs) with respect to changes in manipulated variables (MVs) and disturbance variables (DVs). The control loop calculates future set points for the MVs based on the model and the measured process parameters for CBM production to achieve at least one control objective for the well field. A plurality of output ports provide control signals for implementing the future set points which when coupled to physical process equipment at the plurality of CBM wells control the physical equipment to reach the future set points.