Patent ID: 9701393
Date: 2017-07-11
CPC Classifications: B29C,B29L,B64C,Y02T

Claim:
1. A method for manufacturing a torsion box inner structure of an aircraft lifting surface, wherein the torsion box inner structure includes at least the following components: a front spar, a rear spar, internal reinforcing elements with vertical stiffeners and external elements attachable to leading and trailing edges of the aircraft lifting surface, the method comprises: providing a set of laminated preforms made of a composite material for forming said torsion box inner structure, wherein each of the laminated preforms is configured to be a part of one of the components of the torsion box inner structure; arranging the laminated preforms in a curing tooling and subjecting the arranged laminated preforms to an autoclave cycle to co-cure said laminated preforms to form as a monolithic component the torsion box inner structure, wherein the laminated preforms are arranged vertically in the curing tooling; and demoulding the curing tooling in a vertical direction by providing relative movement in the vertical direction between the curing tooling and the monolithic component.