Abstract

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.

IPC Classes  ?

• B64D 41/00 - Power installations for auxiliary purposes
• B64C 13/38 - Transmitting means with power amplification
• B64D 47/00 - Equipment not otherwise provided for

Abstract

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.

IPC Classes  ?

• B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
• B64F 5/60 - Testing or inspecting aircraft components or systems
• G01M 3/38 - Investigating fluid tightness of structures by using light

Abstract

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.

IPC Classes  ?

• F15D 1/10 - Influencing the flow of fluids around bodies of solid material
• B64C 7/00 - Structures or fairings not otherwise provided for
• B64C 23/06 - Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
• B64D 33/08 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems

Abstract

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.

IPC Classes  ?

• B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
• B64C 25/18 - Operating mechanisms
• B64C 25/26 - Control or locking systems therefor

Abstract

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.

IPC Classes  ?

• B64C 3/00 - Wings

Abstract

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.

IPC Classes  ?

• B64C 25/20 - Operating mechanisms mechanical
• B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways