Airbus Germany

In order to allow an improved weld joint to be manufactured, the invention proposes a system (10, 10', 10") for ultrasonic welding which comprises a sonotrode (11) for emitting ultrasonic energy into a joint region (12) between a first part (13) and a second part (14) that are to be joined together. A consolidator (15; 15') exerts pressure on a surface (16; 17) of one of the first and second parts (13; 14) to consolidate the joint region (12). The consolidator (15, 15') is conformable to the surface (16; 17) of the one of the first and second parts (13; 14) to consolidate the joint region (12).

This fuel tank supporting arrangement (22) for an aircraft, comprises: - an inner support (30), configured for being fastened to a fuel tank (20); and - an outer support (32), configured for being fastened to a fuselage (12) of the aircraft (10); the inner support (30) and the outer support (32) being connected to each other and configured for supporting the fuel tank (20) in the fuselage (12), the inner support (30) and the outer support (32) being configured to be moveable one relative to another along a predetermined path (P) if an acceleration of the fuel tank (20) relative to the fuselage (12) reaches a predetermined excessive acceleration threshold (Ta).

Offenbart sind ein Sandwichelement mit einem Schaumkern, der an seinen zueinander entgegengesetzten Großflächen zumindest jeweils eine Decklage aufweist, wobei in die eine Großfläche des Schaumkern Vertiefungen eingebracht sind und die zumindest eine sich über diese Großfläche erstreckende Decklage mit Öffnungen versehen ist, die sich zumindest teilweise in Überdeckung mit den Vertiefungen befinden, ein Herstellungsverfahren sowie ein Kabinenelement.

A support assembly (10) for a high lift body (8), in particular a leading-edge-slat, configured to be mounted to a spar (6) of a wing (3) of an aircraft (1), as well as a corresponding high lift body arrangement (4), a wing (3) and an aircraft (1) are provided, the support assembly (10) comprising at least two hinging organs (30) each providing at least one hinge point (G) configured for hinging the high lift body (8) at the spar (6) movably between a stowed position (S) and a deployed position (T) along a motion path (E) involving a translatory component (I, J, L) extending within a deployment plane (P) extending transversely with respect to a mounting plane (H) provided by the spar (6) for mounting the hinging organs (30) to the spar (6).

This slat cove filling device (24) for a slat (18) of an aircraft (10) comprises a sheltering panel (46) extending along a spanwise direction (Y) and comprising a proximal edge (50), configured for being fastened to a slat body (22) of the slat (18), and a distal edge (52), configured for being slidable relative to the slat body (22),the sheltering panel (46) comprising a plurality of guiding passages, each guiding passage being configured for cooperating with a guiding element of the slat body (22) for guiding the distal edge (52) along a sliding direction (S) relative to the slat body (22).

Disclosed are a panel element, in particular for use as an aircraft interior part, comprising at least one plate component having a front side and a rear side, and a stiffening structure forming enforced areas of the plate component, wherein the stiffening structure comprises at least an edge protection frame surrounding outer edges of the at least one plate component, and local stiffening elements extending over adjacent surface areas of the front side and the rear side, wherein the stiffening structure is visible in a final state of the panel element on both sides, and an aircraft interior part comprising at least one panel element.

This actuation mechanism (24) is configured for moving a high lift surface (22) relative to a wing body (20) and comprises:- a guiding linkage (26), configured for guiding a displacement of the high lift surface (22) relative to the wing body (20),- a rocker (28), configured to be moveable in rotation relative to the wing body (20);- a rotational actuator (30), comprising a housing (38) and an actuation element (40), the housing (38) being fastened to the rocker (28) and the actuation element (40) being moveable in rotation relative to the housing (38); and- an actuation linkage (32) configured for displacing the rocker (28) and the high lift surface (22) relative to the wing body (20) upon rotation of the actuation element (40) relatively to the housing (38).

Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5) and a leading edge high lift assembly (6) comprising a slat (7), and a connection assembly (9) movably connecting the slat (7) to the main wing (5), such that the slat (7) is movable between a retracted position (11), a first extended position (13), and a second extended position (15), wherein the connection assembly (9) comprises an elongate slat track (17) that extends along a track longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first and second ends (21, 23), wherein the first end (21) and/or the intermediate portion (25) of the slat track (17) is mounted to the slat (7), wherein the slat track (17) is mounted to the main wing (5) by a roller bearing (27) such that the slat track (17) is movable along the track longitudinal axis (19), wherein the roller bearing (27) comprises a plurality of bearing units (34a-c), each of the bearing units (34a-c) being mounted to the main wing (5) and having a bearing surface (22) for engaging an engagement surface (35) provided on the slat track (17), wherein the plurality of bearing units (34a-c) comprises at least a first end roller unit (34a) and an intermediate roller unit (34b), wherein the plurality of bearing units (34a-c) are positioned such that, relative to the track longitudinal axis (19), the intermediate roller unit (34b) is positioned between the first end roller unit (34a) and the second end (23) of the slat track (17). The object to provide a wing having a beneficial ratio of aerodynamic performance and noise generated by extension of the slat, is achieved in that the slat track (17) and the roller bearing (27) are configured such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), whereas in the second extended position (15), a gap (37) is formed between the trailing edge of the slat (7) and the leading edge of the main wing (5).

A wing (3) for an aircraft (1), comprising a main wing (5) and a leading edge high lift assembly (6) comprising a slat (7) and a connection assembly (9) movably connecting the slat (7) to the main wing (5), such that the slat (7) is movable between a retracted position (11), a first extended position (13), and a second extended position (15), wherein the connection assembly (9) comprises an elongate slat track (17) that extends along a track longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first and second ends (21, 23), wherein the first end (21) and/or the intermediate portion (25) of the slat track (17) is mounted to the slat (7), wherein the slat track (17) is mounted to the main wing (5) by a roller bearing (27) such that the slat track (17) is movable along the track longitudinal axis (19). The object to provide a wing having a beneficial ratio of aerodynamic performance and noise generated by extension of the slat, is achieved in that the slat track (17) is mounted to the slat (7) rotatably about a slat axis (22), and the connection assembly (9) comprises a slat angle mechanism (10) mounted to the slat (7) and configured to control the angle of the slat (7) about the slat axis (22) when the slat (7) is moved between the retracted position (11), the first extended position (13) and the second extended position (15).

The invention relates to a drive assembly (2) for driving a movable flow device (4) of an aircraft. The drive assembly comprises a single actuator (10) comprising a longitudinal transmission element (48), a first support element (12) and a second support element (18). The longitudinal transmission element of the single actuator (10) is configured to be oriented transversely to an extending direction of the movable flow device (4), is configured to be mounted to a fixed support structure (6) of the aircraft, and is configured to act on the first and second support elements (12, 18) such that the movable flow device (4) is movable between extended or retracted positions relative to the fixed support structure (6). The invention also relates to a drive system, a high lift system, an aircraft wing, an aircraft and a method of actuating a movable flow device.