Abstract: A leading edge structure (1) for a flow control system of an aircraft (101) including a double-walled leading edge panel (3) with a first side portion (11) extending to a first attachment end (17), a second side portion (13) extending to a second attachment end (19), an inner wall element (21) facing a plenum (7), an outer wall element (23) facing ambient flow (25), and a core assembly (97). The outer wall element (23) includes micro pores (31) and the inner wall element (21) includes openings (33) which form a fluid connection from ambient flow, through the core assembly (97) and to the plenum (7). The thickness of the outer wall element is reduced due to the first attachment end (17) and/or at the second attachment end (19) attached to the inner wall element (21) by both bonding and fasteners (85, 87, 89, 91).

Abstract: A lining for a vehicle part is disclosed. The lining has a main body that comprises a reinforcement. The main body and the reinforcement are made of the same material. The reinforcement may be made of a material removed from the main body. The lining may also include a decorative layer. A method for producing such a lining is also disclosed.

Abstract: A lining for a vehicle part is disclosed. The lining has a main body that comprises a reinforcement. The main body and the reinforcement are made of the same material. The reinforcement may be made of a material removed from the main body. The lining may also include a decorative layer. A method for producing such a lining is also disclosed.