An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

A wingtip device to attach to a wing of an aircraft includes an aerofoil portion and a connection spar arranged to be received in a connection spar receiving portion of the wing of an aircraft. The spar includes a first through hole in a first portion of the connection spar and a second through hole in a second rearward portion of the connection spar, the second portion being rearward of the first portion with respect to a direction of flight. The first and second through holes are arranged to receive a retaining pin that is to be inserted through both the first and second through holes.

A wing assembly include at least one fuel tank having a tank outboard end. In addition, the wing assembly includes a stout wing rib located proximate the tank outboard end and extending between a front spar and a rear spar. The wing assembly also includes at least one outboard wing rib located outboard of the stout wing rib and defining an outboard wing bay. The wing assembly also includes an upper skin panel and a lower skin panel each coupled to the front spar, the rear spar, the stout wing rib, and the outboard wing rib. A plurality of bead stiffeners are coupled to the upper skin panel and/or the lower skin panel and are spaced apart from each other within the outboard wing bay.

Methods and apparatus are disclosed for deployable wing portions of an aircraft. An example method of deploying an aircraft includes separating the aircraft from a launch vehicle, the aircraft having a wing pivotably coupled to a fuselage, rotating, about an axis of rotation, the wing relative to the fuselage from a first rotational orientation to a second rotational orientation different from the first rotational orientation, wherein, in the first rotational orientation, the wing extends along a direction that substantially aligns with a longitudinal axis of the fuselage, and extending the wing in a lateral direction away from the fuselage in the second rotational orientation.

A composite component (16) for a vehicle (10) includes a laminate (18) made from a composite material, a first pad-up area (22) applied to the laminate (18), where the first pad-up area (22) includes a plurality of first tows laid next to one another in a side-by-side arrangement and where the first pad-up area (22) defines a first fiber orientation, and a second pad-up area (24), where the second pad-up area (24) includes a plurality of second tows laid next to one another in a side-by-side arrangement and where the second pad-up area (24) defines a second fiber orientation that differs by a predetermined angle from the first fiber orientation. The first pad-up area (22) and the second pad-up area (22) intersect at an intersecting area and together form a first pad-up ply on the laminate (18).

A rib is disclosed for use in a torque box of a wing structure provided on an aircraft. The wing structure has a skin panel and a stringer coupled to the skin panel. The rib includes a web defining at least one stringer hole sized to receive the stringer, a shear tie coupled to the web and configured to engage the skin panel, and a clip positioned adjacent the at least one stringer hole. The clip has a base coupled to and aligned with the web, a head extending at an angle relative to the base and configured to engage the stringer, and a transition portion extending between the base and the head.

An assembly having a pylon with an upper spar and four lateral scoops, a wing with a skin, longitudinal spars and fittings, and, for each lateral scoop, two fastening assemblies, wherein the skin and the fitting each have a first bore and wherein the upper spar and the lateral scoop each have a second bore, wherein each fastening assembly has a screw passing through the first and the second bores, a nut, two eccentric rings, threaded onto one another and onto the screw, and a system for stopping the eccentric rings rotating. The assembly makes it possible to dispense with the use of the spigots while also ensuring the reaction of the shear forces contained in the XY plane by the bolts on account of the reduced tolerances between the various bores, the external and internal surfaces of the eccentric rings and the plain zones of the screws.

An aircraft propulsion system configured to be supported from an aircraft wing having a leading edge and opposing upper and lower surfaces. The aircraft propulsion system broadly comprises an engine having a core, a fan case, and a nacelle including a plurality of access panels, and an attachment assembly for securing the engine to the aircraft wing. The attachment assembly broadly comprises an upper support section including a number of spars and a number of ribs connected between the spars, a lower support section, and an aft section. The attachment assembly aerodynamically melds the nacelle and the aircraft wing together via the upper support section so that air flowing over the engine flows over the aircraft wing along the upper surface and air flowing laterally alongside the nacelle flows under the aircraft wing along the lower surface.

A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.