Airbus Operations Gmbh

Peter Baker

Chetan Korya

Jonathan Price

Timothy J Sanderson

Stephen Williams

Richard Smith

Gary Wiles

James Eden

Robert James Heath

Graham Morgan

A method of manufacturing an aircraft component, the component comprising a pair of covers joined by a pair of spars. The covers and spars form a closed box structure with four corners, each corner providing a transition between one of the covers and one of the spars. The method comprises: laying up a laminated sheet of fiber plies; and after the sheet has been laid up, folding the sheet to form the four corners and then joining the sheet to itself to provide the closed box structure.

Aircraft component with closed box structure

The present invention provides an aircraft structure comprising a first sub-structure, having a first box cross-section, a second sub-structure, having a second box cross-section, and a joint joining a first end region of the first sub-structure to second end region of the second sub-structure, wherein the joint comprises an overlap region where the end regions of the first and the second sub-structures overlap such that the first sub-structure is inside the second sub-structure. The present invention also provides an aircraft comprising such an aircraft structure and a method of manufacturing an aircraft structure.

Aircraft structure

A curable assembly which upon the application of curing conditions will form a completed component or part component comprises two pieces of composite fiber-reinforced, resin matrix material, with filler component of relatively rigid material arranged therebetween. The intermediate component is arranged to be secured between the two pieces. The filler component has a body with first and second opposing surface profiles. The filler component can be used to transmit or react a consolidating load during curing.

Curable assembly and a filler component

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Bristol, United Kingdom

Peter Baker