Disclosed embodiments include a structurally integrated thermal management system that uses the structure of an aerospace vehicle as part of the heat dissipation system. In this system, structural elements of the aerospace vehicle function as a thermal bus, and are thermally connected with heat-generating electrical components, so that heat from those components is directed away from the component by the structure of the vehicle itself, into lower temperature surfaces of the vehicle.

A structural assembly for an airfoil structure comprising at least one connection member configured to connect a leading-edge member, or a trailing-edge member, of an airfoil structure to a torsion-box member, such that the connection member prevents the leading-edge member, or trailing-edge member, from pivoting relative to the torsion-box member away from an operational position. At least one corresponding support is provided wherein the support is configured to be attachable to the connection member and further configured to be attachable to at least one system element.

An ornithopter includes a main wing mounted on a fuselage. The main wing includes a main spar extending outwardly from the fuselage, and a rib extending rearwardly from the main spar. The rib has an S-shaped camber.

A method for assembling a box structure includes elementary parts assembled along an understructure of stiffeners and skins. The understructure and skins are made of composite material with a polymer matrix. The method includes sizing the box structure for the loads to which it is subjected and for a glued assembly. A map of the loads on the structure is obtained and a first load limit is defined depending on the probability of the structure being damaged. The understructure and the skins are assembled by gluing them. An additional layer is applied that covers the assembled elementary parts to areas of the assembled box structure where the first load limit is reached.

An example aircraft wing includes a skin, a composite shear tie, a stringer base charge overlaying the skin, and a stringer overlaying the stringer base charge. The composite shear tie includes a shear-tie web, a first shear-tie flange extending from a first side of the shear-tie web, a second shear-tie flange extending from a second side of the shear-tie web, and a first shear-tie tab extending from an end of the first side of the shear-tie web. The stringer includes a stringer web, a first stringer flange extending from a first side of the stringer web, and a second stringer flange extending from a second side of the stringer web. The first stringer flange is stitched to and integrated with the stringer base charge and the skin. Further, the first shear-tie flange is stitched to and integrated with the first stringer flange.

A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

A wing assembly includes a center wing structure and a pair of outer wing structures. The center wing structure includes a center wing front spar, a center wing rear spar, and an engine mounting location on each side of a wing centerline. Each outer wing structure includes an outer wing front and rear spar configured to be coupled respectively to the center wing front and rear spar to define a wing joint coupling the outer wing structure to the center wing structure. The center wing structure is configured such that the spar terminal ends of the center wing front and rear spars at each wing joint are located no further inboard than an engine centerline associated with the engine mounting location, and no further outboard of the engine centerline than ten percent of a distance between the engine centerline and the wing centerline.

A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

An aircraft includes a wing with integrated ducted fans and ribs. Each respective ducted fan comprises a duct ring, a guide grille arranged within the duct ring, and an electric motor supported by the guide grille. The ribs are integrated into the guide grille. Each respective electric motor can be cylindrical, and the ribs can run tangentially along the electric motors.

In one aspect, there is a joint member for a composite having a laminate layer including a support member having a first side and a second side; a first flange extending laterally from the first side and having an attachment surface for attachment to a structure; and a second flange extending laterally from the second side and having an attachment surface configured for attachment to the laminate layer. The joint member is configured to provide a load path from the first flange to the second flange. In an embodiment, a joint system for a composite system includes a joint member attached to a first skin and a second skin. In still another embodiment, a joint system for a rib assembly includes a joint member attached to a rib web and rib post.