Abstract: A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

Abstract: An aircraft landing gear bay door 140 including an attachment mechanism suitable for pivotally mounting the door to an aircraft, a first side 141 arranged to face inwardly in relation to the aircraft landing gear bay when the door is closed and face towards one side of a main leg of the landing gear when the door is open and the landing gear is deployed, and a second opposite side 142. The shape formed from the first and second sides provides an aerofoil profile of the door. The invention also provides an aircraft landing gear arrangement 100, an aircraft 1000, methods of operating an aircraft and a method of reducing noise.

Abstract: A movable aerodynamic surface for an aircraft is disclosed including a skin having a first skin portion and a second skin portion both extending from the leading edge to the trailing edge and together surrounding an interior from opposite sides, and a stiffener arrangement arranged in the interior and including at least an inboard stiffener in the area of the inboard end and/or an outboard stiffener in the area of the outboard end. At the inboard end between the first skin portion, the second skin portion and the inboard stiffener an inboard cavity is formed, and/or at the outboard end between the first skin portion, the second skin portion and the outboard stiffener an outboard cavity is formed. An acoustic filler arrangement including multiple filler elements is arranged within the inboard cavity and/or the outboard cavity for reducing noise.

Abstract: A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding surrounds a plenum (17) which extends in a span direction (19), wherein the leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25), wherein the leading edge panel (13) has a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding a plenum (17) that extends in a span direction (19). The leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25) and a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).

Abstract: A leading edge structure (11) for a flow control system of an aircraft (1) including a leading edge panel (13) surrounding surrounds a plenum (17) which extends in a span direction (19), wherein the leading edge panel (13) has a first side portion (21) extending from a leading edge point (23) to a first attachment end (25), wherein the leading edge panel (13) has a second side portion (27) opposite the first side portion (21), extending from the leading edge point (23) to a second attachment end (29), wherein the leading edge panel (13) comprises an inner surface (33) facing the plenum (17) and an outer surface (37) in contact with an ambient flow (39), and wherein the leading edge panel (13) comprises a plurality of micro pores (45) forming a fluid connection between the plenum (17) and the ambient flow (39).

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: The invention relates to a method of gas metal arc welding in which an electric arc burns in a shield gas environment during welding for production of a weld along a welding path between at least one workpiece to be welded and a melting wire electrode (1) that is in particular continuously fed to the at least one workpiece. At the starting end of the weld to be produced, chronologically before ignition of the electric arc between the at least one workpiece and the wire electrode (1), a nonconsumable electrode (2) is moved toward the at least one workpiece. Between the at least one workpiece and the nonconsumable electrode (2), in a shield gas environment an electric arc is ignited that locally preheats the at least one workpiece at the starting ending end of the weld to be produced.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: A fixed wing of an aircraft, having a main wing extending over a half-span with a wing box including spars extending along the spanwise direction of the main wing, ribs arranged one in back of the other viewed in the spanwise direction, and an outer skin. The wing box includes a wing box base section (K10) and a wing box adapter section, that forms the outer end area of the wing box, as viewed from the wing root, and is designed to secure a wing tip device. In its nominal state of construction, the dihedral angle of the wing box adapter section referring to the respective local spanwise direction continuously increases by at most 60 degrees from the outer rib of the wing box base section (K10) up to the outermost rib of the wing box adapter section.

Abstract: A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device.

Abstract: A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device.