Airbus Operations Gmbh

Ivano Bertolini

Jeff Wee Hong Yap

Frank Nielsen

Michael Höft

Nicole Jordan

Martin Obermaier

Stefano Giaquinto

Sebastian Welz

Nina Düren

Sergej Rajkowski

Henrik Lüttmann

Wim Westbroek

A leading edge structure () for a flow control system of an aircraft (), including a leading edge panel () surrounding a plenum () and having a first side portion (), a second side portion (), an inner surface () facing the plenum () and an outer surface () in contact with an ambient flow (), wherein the leading edge panel () includes micro pores (), wherein a first port device () is arranged in the first side portion () fluidly connected to the plenum () via a duct () defined by a duct structure (), and wherein the first port device () comprises a first door () pivotable by a first hinge () about a first hinge axis ().

Leading edge structure for a flow control system of an aircraft

A leading edge structure () for a flow control system of an aircraft (), including a leading edge panel () that surrounds a plenum (), wherein the leading edge panel () has a first side portion (), a second side portion (), an inner surface () and an outer surface (), wherein the leading edge panel () having micro pores () forming a fluid connection between the plenum () and the ambient flow (), wherein a first air inlet/outlet device () is arranged in the first side portion () and a second air inlet outlet/device () is arranged in the second side portion (), fluidly connected to the plenum (), and wherein the first air inlet/outlet device () comprises a pivotable first door () and the second air inlet outlet/device () comprises a pivotable second door ().

A leading edge structure () for a flow control system of an aircraft () including a double-walled leading edge panel () surrounding a plenum (). The leading edge panel () has a first side portion () extending to a first attachment end (), a second side portion () extending to a second attachment end (), an inner wall element () facing the plenum (), an outer wall element () for contact with an ambient flow (), a core assembly (). The outer wall element () includes micro pores () forming a fluid connection between the core assembly () and the ambient flow (). The inner wall element () includes openings () forming a fluid connection between the core assembly () and the plenum (). The outer wall element () extends from the first attachment end () to the second attachment end ().

A leading edge structure () for a flow control system of an aircraft () including a double-walled leading edge panel () with a first side portion () extending to a first attachment end (), a second side portion () extending to a second attachment end (), an inner wall element () facing a plenum (), an outer wall element () facing ambient flow (), and a core assembly (). The outer wall element () includes micro pores () and the inner wall element () includes openings () which form a fluid connection from ambient flow, through the core assembly () and to the plenum (). The thickness of the outer wall element is reduced due to the first attachment end () and/or at the second attachment end () attached to the inner wall element () by both bonding and fasteners ().

To reduce vibration of movable airfoil structures, such as rudders, elevators, and ailerons, a spring device, a leaf spring for example, is mounted to an airfoil mounting structure, such as a vertical tail plane, horizontal tail plane or the wings, such that the spring device exerts a force on a cam device, which transforms the spring force into an airfoil torque. The airfoil torque is applied to the airfoil structure and thus reduces a risk of vibration. The cam device is configured to redirect the spring force such that when the airfoil structure is moved in a first direction, torque decreases and when moved in the opposite second direction the torque is zero.

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Hamburg, Germany

Ivano Bertolini