A wing used for an aircraft includes a configuration member formed of a composite material. The configuration member is divided into a plurality of regions along a surface thereof. The plurality of regions include a first region formed of the composite material of a high strength type, and a second region formed of the composite material of a high elasticity type having higher rigidity than the high strength type. The first region includes any region closest to a wing end side out of the plurality of regions, and the second region includes a region closest to the wing end side and a trailing edge side out of the plurality of regions.

A panel is disclosed, including a first facesheet, a second face sheet, and a plurality of pultrusion-formed web structures. Each web structure has a middle support portion, a first end portion, and a second end portion. The first end portion of each web structure is attached to the first facesheet and the second end portion of each web structure is attached to the second facesheet. The middle support portion, first end portion, and second end portion of each web structure form a single monolithic structure.

An apparatus is proposed for applying and removing protective caps (1) to and from the ends of elongate members (6). The protective cap (1) has a hard base portion (5) and a cover portion (2) of flexible, resilient material, extending from the base portion (5) and operative to cover a portion of an outer surface of the elongate member (6). The apparatus comprises: a gripping mechanism (44) operative to grip the hard base portion (5) of the protective cap (1); a drive mechanism, connected to the gripping mechanism (44), operative to move the protective cap (1) to and from the end of the elongate member (6); and a tool operative to perform at least one of the operations of (i) unfurling the cover portion to secure it to the outer surface of the elongate member, (ii) furling the cover portion to detach it from the outer surface of the elongate member.

A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

A composite core assembly includes a composite core structure having internal material interfaces and an attachment rail coupled to the composite core structure. The attachment rail includes a first planar surface and a second planar surface adjoined with the first planar surface. The first planar surface is arranged parallel to an internal material interface plane of the composite core structure, and the first planar portion is at least partially integrated into the composite core structure in an internal material interface plane. At least a portion of the first planar surface extends beyond a perimeter surface of the composite core structure, and the second planar surface is configured to attach to the surrounding support member. The core material does not have net edge facets or flat edges positioned next to surrounding structure, and/or may not have a structure arranged parallel to the adjacent support structure to attach to the support structure.

A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.

A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.

An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.

An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.

A leading-edge arrangement for a flow body has a curved skin panel having outer and inner sides, and a three-dimensional reinforcing lattice. The curvature of the outer side of the lattice corresponds to the curvature of the inner side of the skin panel. The outer side of the lattice has attachment points connected to the inner side of the skin panel. The lattice is constructed as a three-dimensional framework having a interconnected framework members that form at least one layer of interconnected three-dimensional bodies.