Abstract: A plug for insertion into a blast-tube exit cavity of a gun-blast diffuser comprises a plug front surface, a plug rear surface, a plug side surface that extends between the plug front surface and the plug rear surface, a body, comprising a polyurethane foam, and a substrate, coupled to the body and comprising a conductive nonwoven fabric, impregnated with a polyurethane matrix. The plug front surface of the plug is formed by the substrate. The plug rear surface of the plug is formed by the body. The plug side surface of the plug is formed by the substrate and the body.

Abstract: A plug for insertion into a blast-tube exit cavity of a gun-blast diffuser comprises a plug front surface, a plug rear surface, a plug side surface that extends between the plug front surface and the plug rear surface, a body, comprising a polyurethane foam, and a substrate, coupled to the body and comprising a conductive nonwoven fabric, impregnated with a polyurethane matrix. The plug front surface of the plug is formed by the substrate. The plug rear surface of the plug is formed by the body. The plug side surface of the plug is formed by the substrate and the body.

Abstract: Core structures (120) for composite panels (75) of an aircraft (10), composite panels (75) and aircraft (10) including the core structures (120), and methods (200) of manufacturing the composite panels (75) are disclosed herein. The core structures (120) include a first side (140), a second side (150), and a connecting region (160) that interconnects an upper portion (142) of the first side (140) with an upper portion (152) of the second side (150). The first side (140), the second side (150), and the connecting region (160) at least partially define an antenna housing (62), which defines a housing volume (64) configured to contain an aircraft antenna (60) of the aircraft (10), and an electromagnetic wave transmission region (66) configured to permit electromagnetic waves to pass therethrough.

Abstract: Core structures (120) for composite panels (75) of an aircraft (10), composite panels (75) and aircraft (10) including the core structures (120), and methods (200) of manufacturing the composite panels (75) are disclosed herein. The core structures (120) include a first side (140), a second side (150), and a connecting region (160) that interconnects an upper portion (142) of the first side (140) with an upper portion (152) of the second side (150). The first side (140), the second side (150), and the connecting region (160) at least partially define an antenna housing (62), which defines a housing volume (64) configured to contain an aircraft antenna (60) of the aircraft (10), and an electromagnetic wave transmission region (66) configured to permit electromagnetic waves to pass therethrough.

Abstract: A fused filament fabrication (FFF) machine includes a cabinet defining a build chamber for building a workpiece including a part and a sacrificial tower for the part at a build location. A head assembly has a filament dispenser for dispensing media through a liquefier tip at the build location during a build process. A controller is operably coupled to the head assembly to control the position of the head assembly and dispensing of the media during the build process. The controller periodically moves the head assembly away from the build location to a tip wipe assembly to clean the liquefier tip during a tip wipe process. The controller moves the head assembly from the tip wipe assembly to dispense a sacrificial slug of material away from the part after the tip wipe process before deposition of the material into the part.