Abstract: 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.

Abstract: A side of body carbon fiber reinforced polymer (CFRP) composite rib assembly that is formed by connecting an aft CFRP rib web, a middle CFRP rib web, and a forward CFRP rib web together. The side of body CFRP rib assembly includes a plurality of stiffeners connected to the aft CFRP rib web, the middle CFRP rib web, or the forward CFRP rib web. A first stiffener connects the aft CFRP rib web with the middle CFRP rib web and a second stiffener connected the forward CFRP rib web to the middle CFRP rib web. The stiffeners may be connected via fasteners or may be co-bonded or co-cured with the side of body CFRP rib web. The stiffeners connected to the side of body CFRP rib assembly may include more than one shape and may be aluminum, a thermoset, and/or a thermoplastic.

Abstract: Rotor assemblies for aircraft are described where one or more blades of the rotor assembly includes a blade alignment device that passively orients a blade in response to an airflow around the blade alignment device when the rotor assembly is free-wheeling. One embodiment comprises a method of operating a rotor assembly for aircraft. The method comprises operating the rotor assembly in a free-wheeling state, where the rotor assembly includes a rotary hub that rotates about an axis and a plurality of blades extending radially from the rotary hub. At least one of the plurality of blades includes a blade alignment device. The method further comprises aligning the at least one of the plurality of blades in response to airflow around the blade alignment device when the rotor assembly is in the free-wheeling state.

Abstract: A method of manufacturing an airfoil includes creating a plurality of cavities separated by a plurality of internal ribs in an airfoil forging. At least one hole is drilled in at least one of the plurality of internal ribs with a waterjet drilling tool. At least one hole extends perpendicularly to a wall of the rib.

Abstract: A web component suitable for use with a snap-fit assembly is disclosed herein. The web component includes, but is not limited to, a sheet metal member that has a periphery and a first side and a second side. The sheet metal member also includes a plurality of protrusions that extend from a first surface of the first side and from a second surface of the second side. The plurality of protrusions are disposed proximate a portion of the periphery and are configured to engage a female receiver associated with the snap-fit assembly.

Abstract: A method for the manufacture of a fiber composite component with at least one opening, which is edged by an integral collar, a device for the execution of a method of this type with a mold core, which has at least one convexity for the formation of a component section in the form of a bulge, also a fiber composite component with a multiplicity of openings, each of which is edged by an integral collar.

Abstract: There is provided a wing panel having improved formability at the time when the wing panel is curvedly formed by the peen forming method, and an aircraft main wing provided with the said wing panel. For a stringer member 20, a base part 21 is formed, and the neutral axis position N in the cross-sectional direction is located on the wing panel 11 side from the center position C in the height direction of a web part 22. When the peen forming method is carried out by projecting metal shots to a portion near a flange part 23 in the tip end portion of the stringer member 20, the tensile strain developing in the portion near a flange part 23 acts in a state in which the moment length around the neutral axis position N is kept long.

Abstract: A unitized composite aircraft wing includes upper and lower composite laminate wing skins that have differing stiffnesses and are bonded to a composite grid structure. The grid structure includes grid spars extending in a span-wise direction, and cross beams extending in a chord-wise direction of the wing. The grid spars include caps bonded to the upper and lower wing skins.

Abstract: A hull structure is provided, for use in particular in an aircraft or spacecraft, the hull structure including an outer skin and structural components which are connected to said skin, as well as an inner lining which forms a supporting structure together with the outer skin and the structural components.

Abstract: A structuring construction for an aircraft fuselage is provided having an outer skin as well as a plurality of formers extending at a spacing side by side crosswise to the longitudinal direction of the fuselage wherein at least a partial number of the formers include a main former portion which is channel-like in cross section and the channel edges of which are adjacent to the outer skin and wherein the channel space of the main former portion serves to accommodate at least one supply air line which may be formed, for example, by a separate pipe line.

Abstract: A composite panel having a first skin forming the outer wall of the panel, known as the lower face (1), and a second skin forming part of the inner wall of the panel. The second skin is formed hollow such as to produce an inner reinforcing frame (2) in the form of a half-box structure (3) which, together with the first skin, forms box parts. The aforementioned frame is equipped with a rim (4a, 4b) for fixing to the first skin, a face known as the upper face (5) and connecting side walls (6, 6a, 6b, 6c, 6d, 6e, 7) between the rim (4a, 4b) and the upper face (5) the first and second skins forming a monolithic self-stiffened panel. The half-box frame (2) has perforated sections (8) which are defined by hollow beam sections forming the half-box frame (2).

Abstract: The invention relates to a leading edge mobile flap (16) for a main wing of an aircraft, this flap including an aerodynamic skin (18) that has a bird impact-sensitive frontal area (24), and a rear skin (28) integral with the aerodynamic skin (18), the flap also comprising a plurality of ribs (34) spaced out along a leading edge longitudinal direction (X?). According to the invention, the flap additionally includes, between two directly consecutive ribs, a single rigid bird trajectory-deflecting wall (42) anchored to the skins (18, 28). Furthermore, in a cross-section taken along any plane orthogonal to the direction (X?), the wall (42) forms with a geometric chord (26) of the flap an angle (?1) with a value of less than 45°.

Abstract: There is a Rogallo wing having an aerodynamic sheet having a leading end and a trailing edge. The trailing edge is curved to form a sheet of increasing concavity away from the leading edge. At least two folded edges extend between the leading end and the trailing edge are on opposed sides of the aerodynamic sheet, the two folded edges comprising integral ribs. A wind energy extraction apparatus comprises one or more concentrator wings that react with a flow of wind to induce a drop in static air pressure that is then used to drive one or more impellers and one or more power converters. The one or more concentrator wings are Rogallo wings.

Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear delta wings, vertical winglets, and three levels. The fuselage has a cross-section of substantially rectangular flat shape, being is wide enough to provide lifting force, and includes three levels separated by multi-partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear delta wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at wingtips of the rear delta wings. The first level disposed at a bottom of the three levels includes a cargo bay and a plurality of landing gear bays. The second level disposed at a middle of the three levels includes fuel tank storages. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force.