Method and apparatus for joining aircraft components
2 Assignments
0 Petitions
Accused Products
Abstract
The surface of a moulding tool, for receiving a first aircraft component, for example a spar, is shaped to correspond to the surface of a second aircraft component, for example a wing skin. A gap is defined between the tool and the first component. Resin is drawn into the gap by a suction pump. The resin fills the gap and cures to forma shim. The first and second components, which are in the form of composite material structures, are then joined together without any significant voids being formed therebetween.
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Citations
48 Claims
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1-25. -25. (canceled)
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26. A method of enabling two aircraft components to be joined together, said method including the steps of
providing a first aircraft component having a surface to be joined to a corresponding surface of a second aircraft component, said first and second components being so shaped that if joined there would be a gap defined between said surfaces of said first and second components, providing a resin infusion system comprising a source of resin, effecting flow of said resin from said source of resin into said gap by means of suction, thereby substantially filling said gap with resin, and curing said resin, wherein the flow of the resin out of the gap is restricted by means of a barrier and at least a part of the barrier is formed by a surface of said resin infusion system.
- 41. A shim forming apparatus including a moulding tool having a surface shaped to receive a first aircraft component such that a gap is present between the surface of said moulding tool and said first aircraft component, said surface of said moulding tool being shaped to correspond to a surface of a second aircraft component, the apparatus further including a resin infusion system including a suction pump and a source of resin, the apparatus being so arranged that in use said gap between the surface of the moulding tool and said first aircraft component is filled with resin to form a shim.
- 44. A moulding tool suitable for use in a shim forming apparatus, said moulding tool having a surface shaped to receive a first aircraft component such that a gap is present between said surface of said moulding tool and said first aircraft component, said surface of said moulding tool being shaped to correspond to a surface of a second aircraft component, said moulding tool being so configured that it may be arranged so that, in use, a gap formed between said surface of said moulding tool and such a first aircraft component is filled with resin to form a shim.
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45. A method of joining two aircraft components together, said method including the steps of
providing a first aircraft component formed of a composite material having a surface to be joined to a corresponding surface of a second aircraft component formed of a composite material, said first and second components being so shaped that if joined there would be a gap defined between said surfaces of said first and second components, providing a resin infusion system comprising a source of resin, placing said first aircraft component against a surface of said resin infusion system, effecting flow of said resin from said source of resin into said gap by means of suction, thereby substantially filling said gap with resin, the flow of the resin out of the gap being restricted by means of a barrier, at least a part of said barrier being formed by a surface of said resin infusion system, and said barrier and said first aircraft component being, during the filling of said gap, removably fixed in position relative to each other by means of a pressure difference, curing said resin while between said first aircraft component and said barrier so as to form a shim on said first aircraft component, separating said first aircraft component and said barrier after said resin has cured, and joining said second aircraft component to said first aircraft component and said shim.
Specification