US 12,291,323 B2
Leading edge structure for a flow control system of an aircraft
Frank Nielsen, Hamburg (DE); Martin Obermaier, Hamburg (DE); Michael Höft, Hamburg (DE); Ivano Bertolini, Hamburg (DE); Jeff Wee Hong Yap, Hamburg (DE); and Sergej Rajkowski, Hamburg (DE)
Assigned to AIRBUS OPERATIONS GMBH, Hamburg (DE)
Appl. No. 17/796,461
Filed by AIRBUS OPERATIONS GMBH, Hamburg (DE)
PCT Filed Jan. 27, 2021, PCT No. PCT/EP2021/051862
§ 371(c)(1), (2) Date Jul. 29, 2022,
PCT Pub. No. WO2021/151945, PCT Pub. Date Aug. 5, 2021.
Claims priority of application No. 10 2020 102 325.1 (DE), filed on Jan. 30, 2020.
Prior Publication US 2023/0294819 A1, Sep. 21, 2023
Int. Cl. B64C 21/04 (2023.01); B64C 3/50 (2006.01); B64C 21/06 (2023.01); B64C 21/08 (2023.01); B64C 3/14 (2006.01)
CPC B64C 21/04 (2013.01) [B64C 3/50 (2013.01); B64C 21/06 (2013.01); B64C 21/08 (2013.01); B64C 2003/146 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A leading edge structure for a flow control system of an aircraft, the leading edge structure comprising
a leading edge panel that surrounds a plenum in a curved manner, the plenum extending in a span direction,
wherein the leading edge panel has a first side portion extending from a leading edge point to a first attachment end,
wherein the 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 leading edge panel comprises 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 a first port device is arranged in the first side portion of the leading edge panel,
wherein the first port device is fluidly connected to the plenum via a duct defined by a duct structure,
wherein the first port device comprises a first door pivotable by a first hinge about a first hinge axis between at least two positions of an outlet position, a closed position, and an inlet position,
wherein the leading edge structure comprises a first actuation mechanism configured to actuate the first door for movement between the at least two positions of the outlet position, the closed position and the inlet position,
wherein the first actuation mechanism extends through the duct structure, so that a first part of the first actuation mechanism is arranged inside the duct and a second part of the first actuation mechanism is arranged outside the duct,
wherein the second part of the first actuation mechanism is attached via a hinge to a front spar of an aircraft component to which the leading edge structure is attached, and
wherein the first door is linked via a lever to the first part of the first actuation mechanism and is forward of the front spar.