Abstract: A substrate for an additive manufacturing process, the substrate having a build surface for fusing to a part being formed on the substrate by the additive manufacturing process, wherein the substrate is configured to provide relatively high stiffness in a direction substantially perpendicular to the build surface, while having a low longitudinal stiffness in the plane of the build surface. Also, a method of forming the substrate, a system including the substrate, and use of the system for creating a part by an additive manufacturing process.

Abstract: There is disclosed an aircraft wing rib comprising a structural rib section to which a wing skin can be attached; and a suction conduit to which, in use, a negative pressure can be applied so as to cause air to be drawn through suction holes provided in the outer surface of the wing skin. There is also disclosed an aircraft wing including such a wing rib.

Abstract: For establishment of a laminar attachment line flow, an aircraft wing includes a leading edge including an attachment line, where air impinging on the region flows in a boundary layer spanwise along the leading edge. The leading edge and the attachment line are at least partially formed at first and second slats. The second slat is located adjacent to the first slat in the downstream direction of the attachment line flow, so that the leading edge includes a slat-to-slat junction, where a slat cavity is formed. A duct has a duct entrance at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing. The duct entrance extends around the leading edge and over the range of positions of the attachment line at the slat-to-slat junction.

Abstract: Modern aircraft wings generally have a lower surface the rear part of which is concave over at least some of its length, for additional lift. Sometimes it is desirable to reduce the wing lift, for instance during turbulence. To this end the wing 1 has, located at least partly in or forward of this concave part and forward of the trailing edge, a spoiler device such as a deployable spoiler 20 operable to change between a configuration in which the surface is uninterrupted and one in which the device separates flow, so as to reduce local lift over the concave portion. An actuator 26 can be provided for deploying the spoiler, and an upper spoiler 40 can also be present, operated by the same or a separate actuator. Alternatively the spoiler device can include a flexible or deforming material 120 operable to protrude from the wing surface.

Abstract: For establishment of a laminar attachment line flow, an aircraft wing includes a leading edge including an attachment line, where air impinging on the region flows in a boundary layer spanwise along the leading edge. The leading edge and the attachment line are at least partially formed at first and second slats. The second slat is located adjacent to the first slat in the downstream direction of the attachment line flow, so that the leading edge includes a slat-to-slat junction, where a slat cavity is formed. A duct has a duct entrance at the slat-to-slat junction for receiving spanwise flow along the leading edge of the wing. The duct entrance extends around the leading edge and over the range of positions of the attachment line at the slat-to-slat junction.