Abstract: The undercarriage for aircraft comprises: at least one wheel provided with a rim; a hub carrying the rim; and a motor and gearing for driving the wheel, the motor and the gearing being received, preferably completely, inside the hub.

Abstract: An aircraft having a propeller engine mounted at the rear of the aircraft, on the back thereof, such that the axis of the engine is parallel to the longitudinal axis of the aircraft. The aircraft has a cell, the rear part of which comprises a horizontal empennage and two vertical empennages, positioned one at each end of said horizontal empennage. The propeller is positioned vertically in line with the rear part of the cell, and the rear part of the cell forms a lateral and downward barrier, on each side of a plane of the propeller, that screens an acoustic intensity equal to approximately?5 dB with respect to a maximum acoustic intensity emitted by the engine.

Abstract: Disclosed are methods and systems for cell content alignment. The methods and systems involve retrieving one or more table parameters, the one or more table parameters including size of currently invisible cells in a display window, size of merged cells, the display window size and text size in the merged cells, calculating a position of a text in a visible portion of merged cells based on the table parameters and displaying the text in the merged cells based on the calculated position of the text.

Abstract: An aircraft having reduced environmental impact includes at least one engine with at least one propeller carried, at the rear, on the top of the aircraft with the propeller(s) located in vertical alignment with the rear part of a noise barrier cell and the rear face of a burst zone situated forward of the central part of an empennage box.

Abstract: An aircraft includes a rear vertical tail unit having two tail fins forming, with the rear part of a fuselage, a channel on the back of the fuselage. A turbine engine is arranged on the back of the fuselage so that gas streams generated by the turbine engine penetrate into the channel. The main landing gear of the aircraft is arranged integrally beneath the fuselage. The wings of the aircraft have a slight sweep angle and a large fineness ratio.

Abstract: The aircraft includes at least one engine suitable for propelling the aircraft in flight, at least one motor of an undercarriage, and automatic means arranged to cause the aircraft to taxi under drive directly from the engine, while simultaneously using the motor for taxiing, other than during takeoff or landing.

Abstract: A method according to which an aircraft is moved along the ground by means of at least two separate appliances connected to the aircraft independently from each other or other appliances. A control element is provided for moving an aircraft, said element sending instructions to at least two separate appliances in order to move the aircraft along the ground by means of the appliances. The invention also relates to an appliance for implementing the method, which can communicate with an identical appliance in order to transmit and/or receive at least one datum relating to a position and/or a movement of one of the appliances.

Abstract: A method for controlling at least one appliances for moving aircrafts: at least one appliance connected to an aircraft is driven to a position that is closer to an entry corridor of a take-off runway than an exit corridor of the runway, and, once the appliance or each appliance is separated from the aircraft, the appliance is driven to a position that is closer to an exit corridor of a landing runway than an entry corridor of said runway.

Abstract: Device for driving at least one wheel of an aircraft landing gear, which includes at least one turbine machine incorporated into the landing gear of the aircraft. Advantageously, the turbine machine is a pneumatic turbine.

Abstract: A lighting and/or signalling device for a motor vehicle, comprising an enclosure which is formed by a housing and glass, an opening being provided in the enclosure, wherein it comprises a ventilation duct which extends from the opening, the ventilation duct being closed by a filtering means which is impermeable to fluids and dust, and permeable to gases.

Abstract: A software control method and apparatus for implementing a knowledge-based polymorph undockable toolbar within an object scene. The undockable toolbar can be used to perform actions on objects created and managed by computer software applications. A knowledge-based polymorph undockable toolbar can merges into a relatively small area, tools for executing various commands that would require substantial screen space if represented by standard icons on a toolbar. The present invention can be used to manipulate non-constrained objects or groups of objects included in an assembly that are linked to each other by constraints. The knowledge based polymorph undockable toolbar can also act to reduce the number of user interactions needed to perform a manipulation task.

Abstract: A software control method and apparatus for implementing a knowledge-based polymorph undockable toolbar within an object scene. The undockable toolbar can be used to perform actions on objects created and managed by computer software applications. A knowledge-based polymorph undockable toolbar can merges into a relatively small area, tools for executing various commands that would require substantial screen space if represented by standard icons on a toolbar. The present invention can be used to manipulate non-constrained objects or groups of objects included in an assembly that are linked to each other by constraints. The knowledge based polymorph undockable toolbar can also act to reduce the number of user interactions needed to perform a manipulation task.

Abstract: The undercarriage for aircraft comprises: at least one wheel provided with a rim; a hub carrying the rim; and a motor and gearing for driving the wheel, the motor and the gearing being received, preferably completely, inside the hub.

Abstract: The aircraft includes an undercarriage having an upper portion, at least one wheel for running on the ground, and a shock absorber connecting the wheel to the upper portion. The aircraft also includes a motor for driving the wheel, the motor being rigidly fastened to the upper portion.

Abstract: Described herein is a user interface with a scroll line, comprising a plurality of segments. Each segment points to a unique part in a document identified by a unique identifier. The scroll line underlines the unique identifier of a current part being displayed in a viewable area. A scroll element is provided on the scroll line operable to navigate between parts of the document by moving it across the segments. Each position of the scroll element on the scroll line selects exactly one segment. The scroll element is positioned at a segment on the scroll line pointing to the current part. Selecting and dragging an image of the scroll line away from a current position of the scroll line changes the information being displayed about the scroll line based on the distance between the current position of the image scroll line and an initial position of the scroll line.

Abstract: Aircraft having reduced environmental impact. According to the invention, said aircraft comprises at least one engine (10) with at least one propeller (12, 13) carried, at the rear, on the top of said aircraft with the propeller(s) located in vertical alignment with the rear part (2R) of the noise barrier cell and the rear face (16) of the burst zone (14) situated forward of the central part (8C) of the empennage box (8).

Abstract: Disclosed is an aircraft having a reduced environmental impact. According to the invention, this aircraft comprises at least one engine (7) having at least one propeller (9, 10) supported, at the rear, on the back of the aircraft with the propeller(s) that is/are arranged in line with the rear portion (2R) of the airframe forming a noise-deflecting barrier.

Abstract: The invention concerns an aircraft comprising: a rear vertical tail unit consisting of at least two tail fins (5, 6) forming, with the rear part (7) of said fuselage (4), a channel (8) arranged on the back thereof; and at least one turbine engine (9, 10) arranged on the back of said fuselage (4) so that the gas streams generated by said turbine engine (9, 10) penetrate into said channel (8); and moreover, the main landing gear of said aircraft is arranged integrally beneath the fuselage (in 11); said wings (2, 3) have a slight sweep angle(?); and said wings have a large fineness ratio.

Abstract: The invention relates to an aircraft with low noise, such as during take-off and landing. According to the invention, the aircraft comprises: two wings (2, 3) which have a reverse sweep (?) and which do not support an engine; a rear vertical tail unit consisting of at least two fins (5, 6) and forming a channel (8) together with the rear part (7) of the fuselage (4), which is disposed on the back of same; and at least one turboshaft engine (9, 10) which is disposed on the back of the fuselage (4), such that the gas streams generated by the turboshaft engine (9, 10) enter the channel (8) and such that the downstream noise of the engine (9, 10) is masked laterally and downwardly by said channel. The root sections (11, 12) of the wings (2, 3) are disposed close to the air inlet (15, 16) of the turboshaft engine (9, 10) such that the upstream noise generated thereby is masked laterally and downwardly by said wings (2, 3).

Abstract: A light unit or indicating device for a vehicle (.e.g., a vehicle lighting unit, a vehicle indicating unit, reversing radars and other systems) has a shell, a light contained in the shell, and an electronics card mechanically associated with the shell. The electronics card is connected an electrical power supply and to a multiplexed bus of an on-board network. The card has a controller for the light that allows exchange of commands and information on status of the light unit over the multiplexed bus, and also has an internal bus connected to the controller and the light that allows exchange between them of commands generated by the controller and of the status information of the light unit. The unit may also have an ancillary component for implementing ancillary facilities such as light beam adaptation or automatic adjustment of the orientation of the light beam.