Methods aim to reduce and/or eliminate the need for shims in manufacturing assemblies, such as in manufacturing of aircraft wings. Exemplary methods include predicting a set of predicted manufacturing dimensions within a range of predetermined allowances for a first part, manufacturing the first part, scanning the first part to determine a set of actual manufacturing dimensions for the first part, and at least beginning manufacturing a second part before the scanning the first part is completed. The second part may be manufactured based on the set of predicted manufacturing dimensions for the first part. Once the scan of the first part is completed, the set of predicted manufacturing dimensions may be compared to a set of actual manufacturing dimensions to check for any non-compliant deviances between the predicted and actual manufacturing dimensions. Repairs and local re-scans may be performed in the areas of the non-compliant deviances, which may streamline manufacturing.

Disclosed is a wing in which, while a continuous surface is maintained, a chord length and camber of an airfoil may be modified via only a rotational drive alone, whereby a structure is simple and aerodynamic efficiency may be improved.

An aircraft structural component is described, including an aircraft skeleton component which divides a space along a longitudinal axis of the aircraft skeleton component into two spatial portions arranged on opposite sides of the aircraft skeleton component, and including a fluid conduit component which runs on an outer side of the aircraft skeleton component and fluidically connects the two spatial portions. Also described is an aircraft wing with an aircraft structural component, as well as an aircraft with an aircraft structural component or with an aircraft wing.

A rib foot cleat for sealing around a stringer passing through a rib mouse hole in an aircraft assembly. The rib foot cleat has a body for attaching to a rib at a rib mouse hole and defines a cleat channel configured to be arranged over the stringer. The rib foot cleat also has an injection hole through the cleat body which is in fluid communication with the cleat channel, to allow sealant material to be injected through the injection hole in to the cleat channel for sealing around the stringer.

A system for forming a composite stiffener includes a support surface to support a composite sheet and a sheet-locating device to locate the composite sheet such that a first sheet-portion is supported on the support surface and a second sheet-portion extends beyond the support surface. The system includes a separation device to separate the second sheet-portion from the first sheet-portion to at least partially form a composite charge. The system includes a layup tool including a longitudinal tool-axis and a layup surface configured to receive the composite charge. The layup surface includes a curvature along the longitudinal tool-axis. The system includes a compaction device to compact the composite charge on the layup surface. The system includes a tool-positioning device to position of the layup tool such that a compaction force, applied to the composite charge by the compaction device, is normal to the layup surface.

An arrangement of a structural element for an aerospace vehicle and a battery set. The structural element extends along a longitudinal direction and has a main web, a first flange and a second flange. The flanges extend away from the main web and are defined by flange edges extending along the longitudinal direction. The first flange, the second flange and the main web form a U-shaped profile defining a cavity. The battery set includes a baseplate and at least one battery on the baseplate. The structural element and the battery set are formed such that the baseplate can be releasably attached to the structural element. The baseplate extends between flange edges and the battery is received in the cavity when the battery set is mounted to the structural element. Further, an aerospace vehicle including such an arrangement, a structural element for an aerospace vehicle and a battery set are disclosed.

Methods aim to reduce and/or eliminate the need for shims in manufacturing assemblies, such as in manufacturing of aircraft wings. Exemplary methods include predicting a set of predicted manufacturing dimensions within a range of predetermined allowances for a first part, manufacturing the first part, scanning the first part to determine a set of actual manufacturing dimensions for the first part, and at least beginning manufacturing a second part before the scanning the first part is completed. The second part may be manufactured based on the set of predicted manufacturing dimensions for the first part. Once the scan of the first part is completed, the set of predicted manufacturing dimensions may be compared to a set of actual manufacturing dimensions to check for any non-compliant deviances between the predicted and actual manufacturing dimensions. Repairs and local re-scans may be performed in the areas of the non-compliant deviances, which may streamline manufacturing.

A panel including an outer face sheet; an inner face sheet; a foam disposed between the outer face sheet and the inner face sheet; and a core structure (e.g., a stringer comprising a hat structure) between the foam and the inner face sheet; and between the foam and the outer face sheet. The core structure is protected from impact damage and increases flexural stiffness of the panel on an aircraft wing.

Disclosed is a wing in which, while a continuous surface is maintained, a chord length and camber of an airfoil may be modified via only a rotational drive alone, whereby a structure is simple and aerodynamic efficiency may be improved.

In an example, a composite stringer is described. The composite stringer includes a composite stringer and a base flange. The composite stringer includes a top flange, a first skin flange and a second skin flange configured to be coupled to a support structure, a first web extending between the first skin flange and a first side of the top flange, and a second web extending between the second skin flange and a second side of the top flange. The support structure includes at least one of a skin of a vehicle or a base charge. The base flange includes a bottom surface extending between the first skin flange and the second skin flange. The bottom surface of the base flange is configured to be coupled to the support structure. The base flange also includes a top surface extending between the first web and the second web.