A component is provided that includes a monolithic structure and a fitting element. The monolithic structure includes first and second outer panels, and spars disposed between the first and second outer panels. The width of the monolithic structure extends between a fitting end and a distal end. The spars extend widthwise between the first and second outer panels. The spar fitting end of each spar has a Y-shaped configuration with first and second finger walls, and a channel disposed there between. Both the first and second finger walls have a divergent end and a distal end. The channel has a closed end and an open end defined at the finger wall distal ends. The fitting element has a body with one or more blades extending outwardly therefrom. Each blade is received in and mates with a spar fitting end channel and is bonded to the spar fitting end.

A system and method are provided that enable joined materials to expand and contract at different rates while maintaining a structurally sound connection. A system for joining structures with differing coefficients of thermal expansion includes: a first structural element of a first material having a first coefficient of thermal expansion (CTE); a plurality of flexures each defining a first portion and a second portion and attached at the first portion to the first structural element; and a second structural element of a second material having a second CTE, where the second structural element is attached to the second portion of each of the plurality of flexures, where in response to relative movement between the first structural element and the second structural element, the plurality of flexures bend to accommodate the relative movement.

An assembly having a pylon with an upper spar and two lateral scoops, a wing with a skin and a front spar, port-side/starboard-side front/rear brackets, each with a recess for a nut. The front spar has front/intermediate/rear pleats. Each front bracket is positioned against the front pleat and the intermediate pleat. Each rear bracket is positioned against the intermediate pleat and the skin. For each recess, the associated bracket has an open bore passing through it that opens into the recess. For each recess, the assembly has a fastening bolt having the nut and a screw of which the threaded shank passes through coaxial bores in the front pleat, in the skin, in the upper spar and in the associated lateral scoop, and the open bore, and is screwed into the nut, and of which the head bears against the lateral scoop.

The disclosure provides a penetrating high wing structure of civil aircraft with blended-wing-body, wherein the structure comprises a left wing, a right wing and a high wing penetrating central wing. The left wing and the right wing are symmetrically arranged and connected to two sides of the high wing penetrating central wing through fasteners respectively, and the high wing penetrating central wing is arranged on the top of the main body. The left wing and the right wing both comprise wing ribs and wing spars that are arranged in a crisscross way. The disclosure proposes a penetrating high wing structure, wherein the wing and the body are designed as a whole so that the wings will not damage the continuity of the internal space of the body, which improves the load transfer efficiency of the structure and reduces the fasteners used for connection, thus reducing the weight of the body.

An aircraft includes a battery pack, an internal support structure to support the battery pack in the aircraft, a first bracket rigidly coupling the battery pack to the support structure, and a second bracket rotationally coupling the battery pack to the support structure. The first and second brackets may be located on opposite sides of the battery pack. The internal support structure may be located in a wing of the aircraft and the first and second brackets may be aligned in a fore-aft direction of the aircraft. The internal support structure may be located in a nacelle of the aircraft and the first and second brackets may be aligned along a transverse direction of the aircraft. The second bracket may include two hangers to support a mass of the battery pack in tension.

The present disclosure provides a structural member for a vehicle. The structural member comprises a plurality of finned spar members interlocked with one another, wherein each of the finned spar members include a main body, a plurality of web members extending from a flange, a circuit board formed on the main body, and a bus bar formed on the main body, wherein a compartment is formed between adjacent web members, each compartment being sized to receive a battery.

A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.

An assembly apparatus includes a retainer, a position measurement device, and a machining device. The retainer is configured to hold an assembly. The position measurement device is configured to measure a difference between an intended machining position and an actual machining position of a first coupling hole in a first assembly component. The first coupling hole is capable of being coupled to the assembly. The machining device is configured to form a second coupling hole capable of communicating with the first coupling hole in the assembly based on a reference position set on the assembly and the difference.

An adjustable fixed structure attachment system 200 for an aircraft wing, the attachment system 200 including a bracket 210 having: a wall 212 for connection to a wing box, a protrusion 214 protruding from the wall 212, and a slot 216 extending through the protrusion 214, wherein the slot 216 has a height and a width, and a bush 220 having a bore 222 extending therethrough for receipt of a pin, wherein the bush 222 is insertable into the slot 216 and dimensioned relative to the slot 216 so that the bush 220 is substantially immovable in a width-wise direction of the slot 216, and is moveable in a height-wise direction of the slot 216 to thereby vary a position of the bush 220 within the slot 216.

Systems, devices, and methods including a leading edge tubular member; an upper tubular member; a lower tubular member; one or more upper rib members connected between the leading edge tubular member and the upper tubular member; one or more lower rib members connected between the leading edge tubular member and the lower tubular member; a rigid sandwich shell disposed between the upper tubular member and the leading edge tubular member; and a sandwich shear web disposed between the upper tubular member and the lower tubular member; where the rigid sandwich shell and the sandwich shear web form a D-shape.