Abstract: Systems and methods are provided for trimming and installation. One embodiment is a system for cutting out portions of a fuselage section. The system includes an Inner Mold Line (IML) tool comprising an inner gripping element configured to apply suction to a portion of the fuselage section, and further comprising an outer gripping element configured to apply suction to an area surrounding the portion, an Outer Mold Line (OML) tool configured to operate a cutter to cut the portion out from the fuselage section while suction is applied to the portion and to the area surrounding the portion, and a track that is disposed between the IML tool and the OML tool, wherein the fuselage section is configured to be pulsed in a process direction along the track, such that the fuselage section remains disposed between the IML tool and the OML tool when pulsed in the process direction.

Abstract: The present disclosure provides an inspection system and method for inspecting an optical surface of a laser scanner, the system including a directional optical source and an optical detector. The method includes moving one of the laser scanner or the inspection system to a position in which a beam axis of the directional optical source extends across but does not intersect the optical surface, between the optical surface of and the optical detector. The method further includes emitting a light beam from the directional optical source, across the optical surface so that light from the light beam is incident on debris disposed on the optical surface. The method further includes collecting the light at the optical detector to form an image that indicates presence of the debris on the optical surface of the laser scanner; and generating feedback to alert a user of the presence of the debris.

Abstract: Systems and methods are provided for advancing a fuselage section of an aircraft. One embodiment is a system that includes a series of plates configured to be sequentially affixed along a length of the fuselage section, and a track configured to form a frictional fit with the plates. The track includes drive units configured to form nips retaining the series of plates, and that are configured to advance the fuselage section along the track in a process direction, and indexing elements that are configured to engage with indexing elements at the plates during pauses between operation of the drive units. The system also includes tools configured to perform work on the fuselage section while the indexing elements of the track are engaged.

Abstract: Systems and methods are provided for trimming and installation. One embodiment is a system for cutting out portions of a fuselage section. The system includes an Inner Mold Line (IML) tool comprising an inner gripping element configured to apply suction to a portion of the fuselage section, and further comprising an outer gripping element configured to apply suction to an area surrounding the portion, an Outer Mold Line (OML) tool configured to operate a cutter to cut the portion out from the fuselage section while suction is applied to the portion and to the area surrounding the portion, and a track that is disposed between the IML tool and the OML tool, wherein the fuselage section is configured to be pulsed in a process direction along the track, such that the fuselage section remains disposed between the IML tool and the OML tool when pulsed in the process direction.

Abstract: Systems and methods are provided for advancing a fuselage section of an aircraft. One embodiment is a system that includes a series of plates configured to be sequentially affixed along a length of the fuselage section, and a track configured to form a frictional fit with the plates. The track includes drive units configured to form nips retaining the series of plates, and that are configured to advance the fuselage section along the track in a process direction, and indexing elements that are configured to engage with indexing elements at the plates during pauses between operation of the drive units. The system also includes tools configured to perform work on the fuselage section while the indexing elements of the track are engaged.

Abstract: A method of fabricating a composite item may include dispensing a composite material comprising a reinforcement and a resin. The method may further include energizing an infrared heat source. The infrared heat source may tend to generate a wavelength of electromagnetic radiation that is preferentially absorbed by the reinforcement. The method may additionally include controlling power to the infrared heat source to cause the infrared heat source to emit a wavelength of electromagnetic radiation that is absorbed by the resin to a relatively greater extent than the wavelength of electromagnetic radiation that is absorbed by the reinforcement.

Abstract: A method of fabricating a composite item may include dispensing a composite material comprising a reinforcement and a resin. The method may further include energizing an infrared heat source. The infrared heat source may tend to generate a wavelength of electromagnetic radiation that is preferentially absorbed by the reinforcement. The method may additionally include controlling power to the infrared heat source to cause the infrared heat source to emit a wavelength of electromagnetic radiation that is absorbed by the resin to a relatively greater extent than the wavelength of electromagnetic radiation that is absorbed by the reinforcement.

Abstract: To fabricate a composite item, an infrared heat source is energized and a composite material is dispensed. The composite material includes a reinforcement and a resin. In addition, the composite material is applied to a substrate of previously applied composite material. The infrared heat source is configured to emit a wavelength of electromagnetic radiation that is absorbed by the resin to a relatively greater extent than the wavelength of electromagnetic radiation is absorbed by the reinforcement.

Abstract: To fabricate a composite item, an infrared heat source is energized and a composite material is dispensed. The composite material includes a reinforcement and a resin. In addition, the composite material is applied to a substrate of previously applied composite material. The infrared heat source is configured to emit a wavelength of electromagnetic radiation that is absorbed by the resin to a relatively greater extent than the wavelength of electromagnetic radiation is absorbed by the reinforcement.