Disclosed herein are methods for fabricating a composite structure by forming, via additive manufacturing, a solid-phase component; positioning the solid-phase component and a reinforcement into a mold cavity; and consolidating, in the mold cavity, the solid-phase component, the reinforcement, and a liquid-phase component to form the composite structure.

A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

A wing for an aircraft, comprising a main wing and a slat assembly with a slat and a connection assembly with a slat track. The front end of the slat track is mounted to the slat, and the rear end and/or the intermediate portion of the slat track are mounted to the main wing by a roller or slide bearing. The slat track is movable along the track longitudinal axis. The connection assembly includes a drive unit. The drive unit includes a rotary actuator mounted to the main wing and having at least one drive arm rotatably driven about a rotation axis and drivingly engaging the slat track, and one of the drive arm and the slat track has at least one groove and the other one of the drive arm and the slat track comprises at least one spigot drivingly engaging the groove.

A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.

A high-lift device connection assembly (24) for movably connecting a high lift device (16) to a wing (14) of an aircraft (10) wherein a track (30) is movably guided between main rollers (38, 40, 42, 44). In order to provide an enhanced fall back safety feature in case of a failure of a roller the invention proposes a track catcher (92) to be attached to a structure (26) of the wing (14) and configured to bear a load imposed by the track (30) in case of a main roller failure, wherein the track catcher (92) has at least one first hook element (94, 94-1-94-4) engaged within a first recession (72) at a first side of the track (30) and at least one second hook element (96, 96-1-96-4) engaged with a second recession (74) at the second side of the track (30). Further, the invention relates to a wing and an aircraft equipped with such high-lift device connection assembly (24).

A high-lift device connection assembly (24) for movably connecting a high lift device (16) to a wing (14) of an aircraft (10) wherein a track (30) is movably guided between main rollers (38, 40, 42, 44). In order to provide an enhanced fall back safety feature in case of a failure of a roller the invention proposes a track catcher (92) to be attached to a structure (26) of the wing (14) and configured to bear a load imposed by the track (30) in case of a main roller failure, wherein the track catcher (92) has at least one first hook element (94, 94-1-94-4) engaged within a first recession (72) at a first side of the track (30) and at least one second hook element (96, 96-1-96-4) engaged with a second recession (74) at the second side of the track (30). Further, the invention relates to a wing and an aircraft equipped with such high-lift device connection assembly (24).

A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

A high-lift device includes a flap disposed at a leading edge of a wing, and configured to be retracted in the lower surface and extended toward of the leading edge; a first rotary shaft and a second rotary shaft, the axial direction of the rotary shafts being disposed along the spanwise direction of the wing, respectively; a first link mechanism connected to the first rotary shaft and the flap; and a second link mechanism connected to the second rotary shaft and the flap. When the first link mechanism is driven with the first rotary shaft, the flap is retracted in the lower surface of the leading edge or is extended toward the front of the leading edge. When the second link mechanism is driven with the second rotary shaft, the position or the angle of the flap moved by the first link mechanism is changed.

A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.

A wing for an aircraft including a wing tip section with an inboard section, a fairing in which an opening connecting an exterior of the fairing and an interior of the fairing is formed and which is mounted to the inboard section of the wing tip section, a movable device arranged in the exterior of the fairing, a connecting assembly movably connecting the movable device to the wing tip section such that the movable device is movable between a retracted position and at least one extended position, and a drive mechanism. The connecting assembly includes an actuating element, which extends through the opening and includes a first section, which is arranged in the interior of the fairing and is drivingly coupled to the drive mechanism, and a second section, which is arranged in the exterior of the fairing and coupled to the movable device.