Abrégé

In order to improve the versatility of PCUs (24), the invention proposes a power control unit (24) that can supply hydraulic pressure and mechanical torque. To this end, the power control unit (24) comprises an electric motor (38) that is coupled to a differential output transmission (44) and a hydraulic pump (42). A switchable transmission device (40) allows the torque of the motor (38) to be redirected either to the output transmission (44), e.g. for driving high-lift devices, or to the hydraulic pump (42), e.g. for extending or retracting landing gears.

Classes IPC  ?

• B64D 41/00 - Installations génératrices de puissance pour servitudes auxiliaires
• B64C 13/38 - Dispositifs de transmission avec amplification de puissance
• B64D 47/00 - Equipements non prévus ailleurs

Abrégé

The invention refers to an overheat detection system for an aircraft, the system comprising a first bleed monitoring computer, BMC1, configured to identify leakages in a pneumatic system, the BMC1 including a first optical controller, a second bleed monitoring computer, BMC2, the BMC2 including a second optical controller, an optical fiber link connecting the first optical controller of the BMC1 and the second optical controller of the BMC2 for communication between the BMC1 and the BCM2 and between the first optical controller and the second optical controller, wherein the first and the second optical controllers are configured to detect overheat of the optical fiber link based on a wavelength shift of a modulated optical signal transmitted through said optical fiber link, and transmit signals to the first BMC1 and the second BMC2 based at least on the detected overheat.

Classes IPC  ?

• B64D 45/00 - Indicateurs ou dispositifs de protection d'aéronefs, non prévus ailleurs
• B64F 5/60 - Test ou inspection des composants ou des systèmes d'aéronefs
• G01M 3/38 - Examen de l'étanchéité des structures ou ouvrages vis-à-vis d'un fluide par utilisation de la lumière

Abrégé

The present application relates to a vortex generator. The present application also relates to an aircraft assembly with a hot air exhaust outlet. The aircraft assembly has an assembly surface over which a hot-air exhaust flow from the hot-air exhaust outlet is exhausted. The aircraft assembly also has a vortex generator with a flow surface. The flow surface lies in an air flow over the vortex generator. The flow surface is arranged to interrupt the hot-air exhaust flow and generates a flow vortex to cool the air flow over the assembly surface.

Classes IPC  ?

• F15D 1/10 - Action sur l'écoulement des fluides autour de corps formés d'un matériau solide
• B64C 7/00 - Structures ou carénages non prévus ailleurs
• B64C 23/06 - Moyens permettant d'influencer l'écoulement d'air sur les surfaces des aéronefs, non prévus ailleurs par génération de tourbillons
• B64D 33/08 - Aménagement sur les aéronefs des éléments ou des auxiliaires des ensembles fonctionnels de propulsion, non prévu ailleurs des systèmes de refroidissement des ensembles fonctionnels de propulsion

Abrégé

The invention refers to a method for operating a landing gear system, preferably in a tricycle configuration, wherein main landing gear (MLG) and the nose landing gear (NLG) are operable from a retracted position where they are housed respectively inside landing gear bays, to a fully extended position where they are extended for landing the aircraft. According to the invention, the extension of the nose landing gear (NLG) is delayed in time with respect to the extension of the main landing gear (MLG), and the nose landing gear (NLG) is kept retracted during a major part of the time that the main landing gear doors (MLGD) are extended. In this manner, vibrations on the main landing gear doors are reduced and incidents caused by fatigue are also reduced, with in turn implies that the maintenance cost of the aircraft is greatly reduced.

Classes IPC  ?

• B64C 25/10 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté
• B64C 25/18 - Mécanismes de manœuvre
• B64C 25/26 - Systèmes de commande ou de verrouillage à cet effet

Abrégé

A joint comprising first and second rib components, the first rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface; and the second rib having an abutment surface and a plurality of lugs disposed adjacent to the abutment surface, wherein the abutment surfaces of the respective ribs are abutting and joined with a tension joint, and wherein the lugs are pinned to form a pinned lug joint by aligning respective holes in the plurality of lugs such that the lugs of the first and second ribs are interleaved and have one or more pins passing through the aligned lug holes. The joint may be used for attaching a wing tip device to the outboard end of an aircraft wing.

Classes IPC  ?

• B64C 3/00 - Voilures

Abrégé

An aircraft, aircraft fuselage, aircraft wing and aircraft landing gear are provided. The landing gear (10) comprises a wheeled leg (12) and a series of mounting members (14, 15, 16, 17) to attach the leg to an airframe of the aircraft via respective attachments (14a, 15a, 18, 19). The leg is pivotably movable between a first stowed position within the aircraft and a second deployed position for movement of the aircraft along the ground, and at least one of the attachments (18) is configured to allow retraction movement of the leg to occur about an angularly variable pivot axis and thus avoid obstacles that would be encountered in a conventional retraction path, and also to alleviate forces in the gear that can be caused by four point location of the gear leg.

Classes IPC  ?

• B64C 25/20 - Mécanismes de manœuvre mécaniques
• B64C 25/12 - Atterrisseurs non fixes, p.ex. largables escamotables, repliables ou ayant un mouvement apparenté latéralement