Connecting module between a drive shaft of an engine fan and a rolling-element bearing

A connecting module interposed between a drive shaft of an aircraft engine fan and a rolling-element bearing, wherein the module includes an inner structure attached to the shaft and including a bonnet, and an outer structure attached to the bearing, which is radially supported on a mechanism installed on the inner structure and delimiting a raceway which is complementary to the bonnet so as to form a ball-joint connection kept in a blocked state by a blocking device installed on the inner structure and protruding radially from the bonnet, wherein a mechanism forming a mechanical fuse provides a junction between the device and the bonnet, such that the ball-joint connection is released following fracture of this mechanism forming a mechanical fuse. The radial support mechanism is added to the device.

CONNECTING MODULE BETWEEN A DRIVE SHAFT OF AN ENGINE FAN AND A ROLLING-ELEMENT BEARING

A connecting module interposed between a drive shaft of an aircraft engine fan and a rolling-element bearing, wherein the module includes an inner structure attached to the shaft and including a bonnet, and an outer structure attached to the bearing, which is radially supported on a mechanism installed on the inner structure and delimiting a raceway which is complementary to the bonnet so as to form a ball-joint connection kept in a blocked state by a blocking device installed on the inner structure and protruding radially from the bonnet, wherein a mechanism forming a mechanical fuse provides a junction between the device and the bonnet, such that the ball-joint connection is released following fracture of this mechanism forming a mechanical fuse. The radial support mechanism is added to the device.

STEERING INDICATOR FOR AN AIRCRAFT, IN PARTICULAR A TRANSPORT PLANE, FOR PROVIDING THE THRUST GENERATED BY AT LEAST ONE ENGINE OF THE AIRCRAFT

Display for a computer can operate in direct or mirror view modes, to provide increased screen size, and also a user to change between applications merely by changing his viewing direction

Display comprises a computer monitor (2) that operates in two modes, in a first mode a direct normal image is displayed on the screen, while in a second mode an inverted image is displayed on the screen. Control of mode of operation is by a control system (6) that detects the direction (D, V) in which a user is looking and commands the computer to display the appropriate image. In virtual mode the user sees an image reflected from a mirror (5). The invention relates to both a method and device for displaying virtual or real images on a computer monitor.

CONNECTING HOUSING BETWEEN A MOTOR BLOWER DRIVE SHAFT AND A BEARING BEARING

PILOTAGE INDICATOR FOR AN AIRCRAFT, IN PARTICULAR A TRANSPORT PLANE, FOR PROVIDING THE DRIVE GENERATED BY AT LEAST ONE AIRCRAFT ENGINE

- Indicateur de pilotage pour un aéronef, en particulier un avion de transport, destiné à fournir la poussée engendrée par au moins un moteur de l'aéronef.- L'indicateur de pilotage (1) comporte des moyens d'affichage (4) qui présentent, sur un écran de visualisation (5), un cadran (6) qui est gradué en pourcentage, dont le maximum représente la poussée maximale disponible pour la phase de vol actuelle, dans la configuration actuelle de l'aéronef et pour les conditions anémométriques actuelles, et qui est muni de signes caractéristiques (7, 8), dont les positions sur le cadran (6) représentent respectivement des poussées commandée et effective qui sont exprimées en pourcentage de la poussée maximale. - Pilotage indicator for an aircraft, in particular a transport aircraft, intended to provide the thrust generated by at least one engine of the aircraft - The piloting indicator (1) comprises display means (4) which present, on a display screen (5), a dial (6) which is graduated in percentage, the maximum of which represents the maximum thrust available for the current phase of flight, in the current configuration of the aircraft and for the anemometric conditions current, and which is provided with characteristic signs (7, 8), the positions of which on the dial (6) respectively represent commanded and effective thrusts which are expressed as a percentage of the maximum thrust.

CONNECTING HOUSING BETWEEN A MOTOR BLOWER DRIVE SHAFT AND A BEARING BEARING

L'invention concerne un boîtier de liaison (18) interposé entre un arbre d'entraînement (8) de soufflante de moteur d'aéronef et un palier de roulement (12b), le boîtier comportant une structure intérieure (26) fixée sur l'arbre (8) et présentant une portée sphérique (32), et une structure extérieure (46) fixée au palier (12b), en appui radial sur des moyens (42) prévus sur la structure intérieure et délimitant une piste (48) complémentaire de la portée (32) de manière à former une liaison rotule (50) maintenue dans un état bloqué par un organe de blocage (34) prévu sur la structure intérieure et faisant saillie radialement de la portée (32), des moyens formant fusible mécanique (37) assurant la jonction entre l'organe et la portée (32), de manière à ce que la liaison rotule soit libérée suite à la rupture de ces moyens. Selon l'invention, les moyens de support radial (42) sont pratiqués sur l'organe (34) The invention relates to a connection box (18) interposed between an aircraft engine fan drive shaft (8) and a rolling bearing (12b), the housing comprising an inner structure (26) fixed on the shaft (8) and having a spherical bearing surface (32), and an outer structure (46) fixed to the bearing (12b), bearing radially on means (42) provided on the inner structure and delimiting a track (48) complementary to the bearing surface (32) so as to form a ball joint (50) maintained in a blocked state by a locking member (34) provided on the inner structure and projecting radially from the bearing surface (32), mechanical fuse means ( 37) ensuring the junction between the member and the seat (32), so that the ball joint is released following the rupture of these means. According to the invention, the radial support means (42) are formed on the member (34)

Connecting module between a drive shaft of an engine fan and a rolling element bearing

The invention relates to a connecting module (18) arranged between a drive shaft (8) of an engine fan of an aircraft and a rolling element bearing (12b), said module comprising an inner structure (26) fixed to the shaft (8) and having a bonnet (32), and an outer structure (46) fixed to the bearing (12b) and radially supported on means (42) provided on the inner structure and defining a track (48) complementary to the bonnet (32) in such a way as to form a ball-joint connection (50) maintained in a blocked state by a blocking body (34) provided on the inner structure and projecting radially from the bonnet (32). Means forming a mechanical fuse (37) ensure the junction between the body and the bonnet (32) such that the ball-joint connection is released following the rupture of said means. According to the invention, the radial supporting means (42) are arranged on the body (34).

Connecting module between a drive shaft of an engine fan and a rolling element bearing

Flight indicator for aircraft, in particular a transport aircraft, intended to provide the thrust generated by at least one engine of the aircraft

L'indicateur de pilotage (1) comporte des moyens d'affichage (4) qui présentent, sur un écran de visualisation (5), un cadran (6) qui est gradué en pourcentage, dont le maximum représente la poussée maximale disponible pour 1a phase de vol actuelle, dans la configuration actuelle de l'aéronef et pour les conditions anémométriques actuelles, et qui est muni de signes caractéristiques (7, 8), dont les positions sur le cadran (6) représentent respectivement des poussées commandée et effective qui sont exprimées en pourcentage de la poussée maximale. The piloting indicator (1) comprises display means (4) which have, on a display screen (5), a dial (6) which is graduated in percentage, the maximum of which represents the maximum thrust available for 1a current flight phase, in the current configuration of the aircraft and for the current anemometric conditions, and which is provided with characteristic signs (7, 8), the positions of which on the dial (6) represent respectively commanded and effective thrusts which are expressed as a percentage of maximum thrust.

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