Airbus Operations Gmbh

Christopher Payne

Llifon Williams

Xavier Hue

Antony Charles Peacock

Heinz Hansen

Risto Kallinen

Ross Salisbury

Simon W Topping

Robert McCormick

Raymond Bullock

Peter Griggs

Glenn Watson

David Groves

Hugh Theobald

Martin Mayneord

David Belfourd

Marcus Rafla

Timothy Evans

Robert Mccormick

Simon Topping

A leading edge structure for providing an aerodynamic surface of an aircraft is disclosed having a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The disclosure is also related to an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.

Leading edge structure

An aircraft wing has a main wing element with a spar and a leading edge rib supported by the spar, a high lift device movably mounted to the main wing element, and an actuation mechanism with a drive shaft and a gear train. The gear train has a drive cog carried by the drive shaft, an actuator cog coupled to the high lift device, and one or more intermediate cogs mounted to the rib and coupled in series with the drive cog and the actuator cog so as to transmit torque from the drive cog to the actuator cog which moves the high lift device between a retracted position and an extended position in which the high lift device increases the camber of the wing. Sizes of the cogs in the gear train are selected so that the drive shaft rotates at a higher rate than the high lift device.

Leading edge rib assembly

An aircraft wing cover () comprising an integrally stiffened sandwich panel including first and second skins () sandwiching a core layer (), wherein at least one of the skins has a plurality of spanwise extending integral regions of increased thickness () accommodated by corresponding regions () of decreased thickness in the core. Also, a method of fabricating an aircraft wing cover, and a method of designing an aircraft wing.

Aircraft wing cover comprising a sandwich panel and methods to manufacture and design the said wing cover

An aerofoil structure () comprising at least two spars () spaced apart in a fore and aft direction so as to define a fuel carrying volume between the spars, and at least one longitudinal corrugated reinforcing member () disposed between the spars, each reinforcing member being corrugated in the longitudinal direction to form a series of forward ridges () on a forward side of the reinforcing member and a series of aft ridges () on an aft side of the reinforcing member, wherein each reinforcing member is directly attached by its forward ridges to one of the spars or to the aft ridges of an adjacent one of the reinforcing members, and wherein each reinforcing member is directly attached by its aft ridges to one of the spars or to the forward ridges of an adjacent one of the reinforcing members. Also, a method of manufacturing an aerofoil structure. The reinforcing member(s) may extend substantially the entire length of the structure to reduce the number of manufactured parts of the structure, increase the stiffness of the structure and reduce the weight of the structure.

Aerofoil structure

A fitting for joining a first component to a second component, the fitting comprising a composite part and a reinforcement element. The composite part is formed from a composite material and comprises: a base; an end wall meeting the base at a first corner; and a side wall meeting the end wall at a second corner and the base at a third corner. The reinforcement element is shaped such that it can be fitted to the composite part and engage the end wall of the composite part, the first corner of the composite part; and the second corner of the composite part.

Fitting

Growing community of inventors

Bristol, United Kingdom

Christopher Payne