Abstract: According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone.

Abstract: Methods of manufacture include welding two or more elongate members together to define an elongate weldment, wherein the welding results in a weld region that is in tension and regions adjacent to the weld region that are in compression, and longitudinally stretching the elongate weldment. Tools and systems for manufacturing elongate weldments, as well as apparatuses, such as aircraft, that include elongate weldments, also are disclosed.

Abstract: A laminated composite radius filler for a composite structure has a stacked ply assembly having a plurality of stacks of laminate radius filler plies cut to a desired width and having a desired ply orientation. The laminated composite radius filler further has a geometric shaped filler element positioned at a desired location on a first portion of the stacked ply assembly. The geometric shaped filler element deforms a second portion of the stacked ply assembly stacked over the geometric shaped filler element, such that the laminate radius filler plies of the second portion of the stacked ply assembly change direction and have a component of direction including a horizontal direction and a vertical direction. The laminated composite radius filler having a shape substantially corresponding to a radius filler region of the composite structure.

Abstract: A laminated composite radius filler for a composite structure has a stacked ply assembly having a plurality of stacks of laminate radius filler plies cut to a desired width and having a desired ply orientation. The laminated composite radius filler further has a geometric shaped filler element positioned at a desired location on a first portion of the stacked ply assembly. The geometric shaped filler element deforms a second portion of the stacked ply assembly stacked over the geometric shaped filler element, such that the laminate radius filler plies of the second portion of the stacked ply assembly change direction and have a component of direction including a horizontal direction and a vertical direction. The laminated composite radius filler having a shape substantially corresponding to a radius filler region of the composite structure.

Abstract: Methods of manufacture include welding two or more elongate members together to define an elongate weldment, wherein the welding results in a weld region that is in tension and regions adjacent to the weld region that are in compression, and longitudinally stretching the elongate weldment. Tools and systems for manufacturing elongate weldments, as well as apparatuses, such as aircraft, that include elongate weldments, also are disclosed.

Abstract: Apparatus tests the performance of joints between an attachment and a beam having a pair of caps connected by a corrugated web. The apparatus includes first and second grips contoured to the shape of a portion of the corrugated web for gripping the web. A force applicator coupled with the attachment and the grips applies force to the beam through the joint.

Abstract: Composite panels used in aircraft are formed by a sandwich including a lightweight honeycomb core reinforced by a solid plank in medial regions of the panel. The plank is bonded to the honeycomb and forms an integral part of the core where a strut is attached to the panel. The plank distributes point loads imposed on the panel by the strut.

Abstract: Apparatus tests the performance of joints between an attachment and a beam having a pair of caps connected by a corrugated web. The apparatus includes first and second grips contoured to the shape of a portion of the corrugated web for gripping the web. A force applicator coupled with the attachment and the grips applies force to the beam through the joint.

Abstract: Apparatus tests the performance of joints between an attachment and a beam having a pair of caps connected by a corrugated web. The apparatus includes first and second grips contoured to the shape of a portion of the corrugated web for gripping the web. A force applicator coupled with the attachment and the grips applies force to the beam through the joint.

Abstract: An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed.

Abstract: A laminated composite rod includes a rod body having a generally circular or oval cross-section and comprising a plurality of laminated composite plies disposed at various orientations with respect to each other.

Abstract: Apparatus tests the performance of joints between an attachment and a beam having a pair of caps connected by a corrugated web. The apparatus includes first and second grips contoured to the shape of a portion of the corrugated web for gripping the web. A force applicator coupled with the attachment and the grips applies force to the beam through the joint.

Abstract: An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed.

Abstract: Composite panels used in aircraft are formed by a sandwich including a lightweight honeycomb core reinforced by a solid plank in medial regions of the panel. The plank is bonded to the honeycomb and forms an integral part of the core where a strut is attached to the panel. The plank distributes point loads imposed on the panel by the strut.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.

Abstract: A laminated composite (multi-ply) radius filler includes a plurality of woven fabric reinforced plies cut to fill a radius gap (including, if appropriate, intentional overfill) to increase absolute strength, to increase specific strength, or to reduce cost by reducing cracking and distortion in the radius of a composite assembly. The present invention also describes the method of manufacture and method of use for such laminated composite radius filler.