Airbus Operations Gmbh

Airbus UK Limited

Leung Choi Chow

Christopher Neil Wood

Philip Campbell

David Leonard Rondeau

David A Foot

David Angland

Xin Zhang

Michael Goodyer

Matthew Spiteri

Andrew John Dyer

An aircraft landing gear assembly comprises a landing gear () arranged to be moveable between a stowed position and a deployed position. The assembly includes a removably mounted cover plate () that covers a void () defined by a part of the landing gear assembly. The plate () may have a substantially constant thickness, one or more fixing elements () on one side only of the plate, and a sealing element () that extends around substantially the entire perimeter () of the plate ().

Landing gear with noise reduction apparatus

An aircraft noise-reduction apparatus comprise a flow-facing element () and a flow control device () positioned downstream of the flow-facing element (). The flow control device () is arranged, in use, to reduce noise induced by unsteady flow downstream of the flow-facing element ().

Splitter plate for aircraft noise reduction apparatus

An aircraft landing gear () includes a wheel () having a wheel rim () on which a tire () is held. The gap () between the rim () and tire () is bridged and covered by a sealing element (), which thereby presents a smooth surface to the air flowing over the wheel during flight of the aircraft (). Thus, noise that would otherwise be generated by the interaction of air and the parts of the wheel () and/or tire () defining the gap () is reduced. Such noise reduction benefits may also be achieved by providing a tire () and wheel () so shaped that there is no gap () between the tire () and wheel rim ().

Landing gear assembly

An aircraft noise reduction apparatus includes an aircraft landing gear assembly and a noise reduction fairing. The landing gear assembly includes a landing geararranged to be moveable between a stowed position and a fully deployed position. The noise reduction fairingmay include a wrap-around fairing which, when the landing gearis in its fully deployed position, wraps around the landing gearand extends along the majority of the length of a landing gear leg. A landing gear bay door assemblyincluding at least one door may also be provided. The fairingmay have a recessfor accommodating one of landing gear bay doors when the dooris in its fully open position.

Landing gear with noise reduction fairing

An aircraft landing gear is described including a noise-reducing means. In one embodiment there is a noise-reducing element that includes an air-deflecting surface, in the form of a fairing, and a perforated airflow-reducing region. In use, some air passes through the perforations, while other air is deflected by the fairing away from a noise-generating region of the landing gear. Noise caused by the passing of the landing gear through the air is therefore reduced. In another embodiment a noise-reducing layer in the form of a mesh is supported by a skeleton structure.

Landing gear

An aircraft landing gear () includes a torque link set () comprising a first fairing () rotatably connected at a first end () to a first end () of a second fairing (). The fairings (), () may be arranged to act as first and second torque links. The fairings may be in the form of noise reduction fairings.

Torque link set

The invention relates to aircraft noise reduction apparatus, in particular, but not exclusively, to noise reduction apparatus on an aircraft landing gear. The aircraft noise reduction apparatus comprises a noise reduction attachment for a landing gear of an aircraft. The noise reduction apparatus is movable between a first position in which it deflects air away from a noise inducing component of the landing gear and a second position in which it allows access to the noise inducing component. The movement of the noise reduction attachment between the first and second positions is actuated by a part of the landing gear.

Aircraft noise reduction apparatus

An aircraft landing gearincludes a folding side stay, wherein the folding side stay includes an integral locking mechanism and does not require the landing gear to include a lock stay. The lack of a lock stay reduces the airframe noise created by the aircraft, which is particularly significant when the aircraft is landing. The aircraft landing gearis movable between an stowed and deployed position. The folding side staycomprises a first section and a second section foldable relative to the first section. The integral locking mechanismis arranged to lock the first section and second section of the folding side stay into position when the landing gear is in the deployed position.

An aircraft landing gear door assembly includes a door, which is moveable to an open position, in which an aperture is exposed, the landing gear being able to be deployed through said aperture, and moveable to a closed position, in which the door is closed across the aperture. The door is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door is also arranged for movement of a second type, different from the first type, in which the door rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof. In one embodiment, the second type of movement is rotational movement about an axis that is substantially parallel to the door when in the closed position and the door forms a ramp type fairing. In another embodiment, the second type of movement is rotational movement about an axis that is substantially transverse to the door when in the closed position and the door forms a V-shaped fairing (when viewed from above) with an opposite door.

Aircraft landing gear and door assembly

An aircraft landing gear () is described including a noise-reducing element that includes an air-deflecting surface, in the form of a fairing (), and a perforated airflow-reducing region (). In use, some air passes through the perforations, whilst other air is deflected by the fairing away from a noise-generating region of the landing gear. Noise caused by the passing of the landing gear through the air is therefore reduced.

Landing gear noise reduction

An aircraft landing gear door assembly () includes a door (), which is moveable to an open position, in which an aperture () is exposed, the landing gear () being able to be deployed through said aperture (), and moveable to a closed position, in which the door () is closed across the aperture (). The door () is arranged for rotational movement of a first type, in which the door rotates about an axis that is substantially parallel to the length of the aircraft, between the closed position and the open position. The door () is also arranged for movement of a second type, different from the first type, in which the door () rotates, about an axis that is substantially transverse to the length of the aircraft, to a position in which it acts as a fairing to reduce the noise caused by the landing gear or a part thereof. In one embodiment, the second type of movement is rotational movement about an axis that is substantially parallel to the door when in the closed position and the door () forms a ramp type fairing. In another embodiment, the second type of movement is rotational movement about an axis that is substantially transverse to the door when in the closed position and the door () forms a V-shaped fairing (when viewed from above) with an opposite door ().

Landing gear door assembly

An aircraft, aircraft landing gear and apparatus including at least one attachment ( ) for noise reduction purposes are provided. Such attachments are shaped and positioned on the landing gear to deflect air away from noise-inducing components ( ) of the landing gear and to permit deflection and articulation movement and also stowage of the landing gear whilst the attachments are installed thereon. The attachments are not designed to be drag-reducing.

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Bristol, United Kingdom

Leung Choi Chow