Abstract: A composite charge used to compression form a stringer comprises multiple plies of unidirectional, prepreg having various fiber orientations. Certain of the plies have a pattern of angled cuts allowing the plies to stretch both longitudinally and transversely during forming, thereby reducing ply wrinkling in contoured areas of the stringer.

Abstract: A composite charge used to compression form a stringer comprises multiple plies of unidirectional, prepreg having various fiber orientations. Certain of the plies have a pattern of angled cuts allowing the plies to stretch both longitudinally and transversely during forming, thereby reducing ply wrinkling in contoured areas of the stringer.

Abstract: Multi-ply composite charges are laid up by a multi-head laminator in a single pass, enabling high rate production of composite laminate structures such as stringers.

Abstract: Systems and methods are provided for hardening wing panel preforms. One embodiment is a method for fabricating a wing panel for an aircraft. The method includes loading a wing skin preform onto a contour of an Outer Mold Line (OML) tool, applying stringer preforms to troughs of an Inner Mold Line (IML) tool, aligning the OML tool with the IML tool, and assembling the IML, tool and the OML tool into a cartridge that molds a wing panel preform comprising the wing skin preform and the stringer preforms. The method further includes inserting the cartridge into a press, and hardening the wing panel preform into a composite part while the cartridge resides in the press.

Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: A manufacturing system employing a bifurcated backbone having an upper plate and lower plate, with a longitudinal slot between the upper and lower plate. A plurality of actuator groups are mounted longitudinally adjacent the slot. A carrier supports a panel for longitudinal translation into the slot and the carrier is configured to pulse longitudinally in the slot relative to the plurality of actuator groups during a sequence of fabrication operations by the plurality of actuator groups on the panel.

Abstract: Systems and methods are provided for hardening wing panel preforms. One embodiment is a method for fabricating a wing panel for an aircraft. The method includes loading a wing skin preform onto a contour of an Outer Mold Line (OML) tool, applying stringer preforms to troughs of an Inner Mold Line (IML) tool, aligning the OML tool with the IML tool, and assembling the IML, tool and the OML tool into a cartridge that molds a wing panel preform comprising the wing skin preform and the stringer preforms. The method further includes inserting the cartridge into a press, and hardening the wing panel preform into a composite part while the cartridge resides in the press.

Abstract: A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: A manufacturing system employing a bifurcated backbone having an upper plate and lower plate, with a longitudinal slot between the upper and lower plate. A plurality of actuator groups are mounted longitudinally adjacent the slot. A carrier supports a panel for longitudinal translation into the slot and the carrier is configured to pulse longitudinally in the slot relative to the plurality of actuator groups during a sequence of fabrication operations by the plurality of actuator groups on the panel.

Abstract: A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

Abstract: A method and an apparatus are presented. The method locally compensates for cure related deformations in a composite skin by laying up a composite material on a compensation surface of a slip sheet designed to form a modified outer mold line different from a designed shape, wherein the slip sheet is held against a forming surface of a layup tool, wherein the forming surface is designed to form an outer mold line of the designed shape.

Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: Systems and methods are provided for structurally supporting an aircraft wing. The system comprises a section of aircraft wing that includes skin. The skin surrounds an internal volume of the wing and comprises layers of Carbon Fiber Reinforced Polymer (CFRP) having fiber orientations aligned to bear shear stresses applied to the wing. The section of aircraft wing also includes planked stringers that are laterally oriented within the wing, contact the skin within the internal volume, are attached to the skin, and comprise layers of CFRP having fiber orientations that are aligned to bear bending at the wing. Furthermore, the section includes spars that are positioned between planked stringers on an upper portion of the wing and planked stringers on a lower portion of the wing, wherein the spars are aligned with the planked stringers.

Abstract: An apparatus, a vehicle and a method for securing intermodal cargo containers is provided. Couplers include pins and bottom supports to engage apertures and bottom surfaces of corner fittings for intermodal cargo containers. The couplers may also include sidewall supports to engage forward facing side surfaces of the corner fittings. The pins, bottom supports, and sidewall supports hold an intermodal cargo container in place through a relatively large range of acceleration forces without damaging the corner fittings of the intermodal cargo containers. The couplers are selectively movable from a retracted position to an extended position to engage the corner fittings of the intermodal cargo containers.

Abstract: A method and apparatus for forming a sandwich structure is presented. A sandwich structure comprises a metallic core layer and a thermoplastic layer on a first side of the metallic core layer. The thermoplastic layer is consolidated against the first side of the metallic core layer.

Abstract: A method for determining material failure that includes the steps of: fabricating a coupon made of a material; applying first force and second forces on the coupon, where the second force is different than the first force; and characterizing a material failure due to the application of the first force and the second force to the coupon.