Patent ID: 11932388
Assignee: AIRBUS OPERATIONS LIMITED
Field: Transport (Mechanical engineering)
Classification: CPC B  Y | IPC B

Claim 0:
1. A leading edge structure for a flow control system of an aircraft comprising:
a double-walled leading edge panel that surrounds a plenum in a curved manner, the plenum extending in a span direction of the leading edge structure;
wherein the double-walled leading edge panel has a first side portion extending from a leading edge point to a first attachment end,
wherein the double-walled leading edge panel has a second side portion opposite the first side portion, extending from the leading edge point to a second attachment end,
wherein the double-walled leading edge panel comprises an inner wall element facing the plenum and an outer wall element for contact with an ambient flow,
wherein between the inner and outer wall elements the double-walled leading edge panel comprises a core assembly,
wherein the outer wall element comprises a plurality of micro pores forming a fluid connection between the core assembly and the ambient flow,
wherein the inner wall element comprises openings forming a fluid connection between the core assembly and the plenum,
wherein at the first attachment end and/or at the second attachment end the outer wall element is attached to the inner wall element by both bonding and fasteners,
wherein a back wall forms a back of the plenum and spanning between the first side portion and the second side portion, and
wherein the fasteners attach the back wall to the outer wall element and the inner wall element at the first attachment end and/or the second attachment end.