Abstract: A composite structure includes a first composite skin and a second composite skin spaced from the first composite skin. The first composite skin and the second composite skin define a longitudinal cavity therebetween. The composite structure further includes a plurality of spars located in the longitudinal cavity and laterally spaced from one another. The plurality of spars extends between and connects the first composite skin and the second composite skin. The composite structure further includes at least one rib located within the longitudinal cavity between a first spar and a second spar of the plurality of spars. The first spar is laterally adjacent the second spar. The at least one rib is in contact with the first composite skin, the second composite skin, the first spar and the second spar.

Abstract: The present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components. More particularly, the present disclosure provides assemblies, systems and characterization methods of welded joints for thermoplastic components (e.g., thermoplastic-based fiber-reinforced composites) utilizing visualization agents (e.g., pigments and/or fluorescent agents). The present disclosure provides for assemblies, systems and characterization methods of welded joints for thermoplastic components and/or thermoplastic-based composites with enhanced visualization, sufficient for qualitative and quantitative assessment of the welded interconnected areas.

Abstract: A composite structure includes a first composite skin and a second composite skin spaced from the first composite skin. The first composite skin and the second composite skin define a longitudinal cavity therebetween. The composite structure further includes a plurality of spars located in the longitudinal cavity and laterally spaced from one another. The plurality of spars extends between and connects the first composite skin and the second composite skin. The composite structure further includes at least one rib located within the longitudinal cavity between a first spar and a second spar of the plurality of spars. The first spar is laterally adjacent the second spar. The at least one rib is in contact with the first composite skin, the second composite skin, the first spar and the second spar.

Abstract: A composite structure includes a first composite skin and a second composite skin defining a longitudinal cavity therebetween. The first composite skin and the second composite skin further define at least one edge where the first composite skin contacts the second composite skin. The composite structure further includes at least one core disposed within the longitudinal cavity. The core includes a first surface and a second surface which define a core edge where the first surface contacts the second surface. The core is positioned with the core edge adjacent the at least one edge with the first surface contacting the first composite skin and the second surface contacting the second composite skin.

Abstract: A propulsion assembly includes a fan and a fan case system disposed about the fan. The fan case system includes at least one perforated portion including a plurality of holes. The propulsion assembly further includes at least one acoustic panel mounted to the exterior surface of the fan case system coincident with the at least one perforated portion. The at least one acoustic panel includes a core including a plurality of cells extending between a first side of the core and a second side of the core. The at least one acoustic panel further includes a back skin attached to the second side of the core. The first side of the core is in contact with the exterior surface of the fan case system to form a plurality of resonant cavities defined by the plurality of holes, the plurality of cells, and the back skin.

Abstract: A propulsion assembly includes a fan and a fan case system disposed about the fan. The fan case system includes at least one perforated portion including a plurality of holes. The propulsion assembly further includes at least one acoustic panel mounted to the exterior surface of the fan case system coincident with the at least one perforated portion. The at least one acoustic panel includes a core including a plurality of cells extending between a first side of the core and a second side of the core. The at least one acoustic panel further includes a back skin attached to the second side of the core. The first side of the core is in contact with the exterior surface of the fan case system to form a plurality of resonant cavities defined by the plurality of holes, the plurality of cells, and the back skin.

Abstract: A nacelle inlet structure for an engine includes a composite inlet lip defining a leading edge of a nacelle of the engine.

Abstract: Aspects of the disclosure are directed to a system that includes a boot configured to attach to a chevron of an aircraft nacelle, and an attachment mechanism configured to attach the boot and the chevron. In some embodiments, a boot includes a first surface and a second surface, where the surfaces are attached by inwardly tapering sidewalls that form an opening that is configured to surround a chevron of an aircraft nacelle. In some embodiments, a repair of a chevron on an exhaust nozzle of an aircraft engine includes placing a chevron-shaped boot with a pocket over at least a portion of a chevron structure on an exhaust nozzle of an aircraft engine, the pocket having a shape that generally conforms to an external surface of the chevron, covering the portion of the chevron structure with the boot, and fastening the boot to the chevron through at least one of bonding or mechanical fastening.

Abstract: Aspects of the disclosure are directed to a system that includes a boot configured to attach to a chevron of an aircraft nacelle, and an attachment mechanism configured to attach the boot and the chevron. In some embodiments, a boot includes a first surface and a second surface, where the surfaces are attached by inwardly tapering sidewalls that form an opening that is configured to surround a chevron of an aircraft nacelle. In some embodiments, a repair of a chevron on an exhaust nozzle of an aircraft engine includes placing a chevron-shaped boot with a pocket over at least a portion of a chevron structure on an exhaust nozzle of an aircraft engine, the pocket having a shape that generally conforms to an external surface of the chevron, covering the portion of the chevron structure with the boot, and fastening the boot to the chevron through at least one of bonding or mechanical fastening.

Abstract: Apparatus for stabilizing a test specimen in a compression/tension testing machine. The apparatus supports the test piece along its lengthwise edge or edges to prevent unwanted Euler buckling, however in a manner so as not to prevent sublaminate buckling. In one embodiment the apparatus supports the test piece along both of its lengthwise edges while engaged between the grips of the test machine. In a second embodiment, the apparatus supports the test piece along only one of its lengthwise edges. In a third embodiment, the apparatus includes grip plates which are mounted to the test machine and which engage a portion of the test specimen while the remainder of the specimen is supported along its lengthwise edges by stabilizer plates.

Abstract: A missile body and related method for producing a missile body comprising a plurality of coaxially disposed contiguous body sections wherein each body section is a structure having a cross-sectional configuration corresponding to a respective cross section of the missile body, means for fixedly attaching the contiguous body sections together axially to form a hull, and an outer skin physically engaging the hull and constituting the outer skin of the missile body.