An indexing apparatus includes a fixture tool, movable relative to an operation cell, and an indexing feature, fixed relative to the fixture tool. The indexing apparatus also includes a plurality of probes, configured to engage the indexing feature. The indexing apparatus further includes a controller, in communication with the plurality of probes, wherein the controller is configured to locate the fixture tool relative to the operation cell from a plurality of probe locations of the plurality of probes, engaged with the indexing feature.

Systems and methods are provided for assembling an airframe of an aircraft, including receiving a half barrel section of fuselage, advancing the half barrel section in a process direction across multiple stations to separately and simultaneously perform work on the half barrel sections, and subsequently joining the half barrel segments to form a section of the airframe. Each pair of half barrel sections, such as upper and lower half barrels, are progressed through assembly line processes to be delivered to a joining station for joining the half barrels together to form a circumferential section of the fuselage. Multiple joined circumferential sections are joined together to form an elongated extent of the fuselage. Indexing features are provided in the assembly process to monitor and control the progression of the half barrel sections in the work stations of the assembly line process.

Systems and methods are provided for aircraft assembly. The method includes receiving a half barrel section of fuselage in an assembly line having a plurality of serially arranged work stations; advancing the half barrel section in a process direction through the assembly line such that the half barrel section extends across at least a portion of the work stations; and performing work on the half barrel section with the portion of the work stations simultaneously.

Systems and methods are provided for fabricating a preform for a fuselage section of an aircraft. The method includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Systems and methods are provided for assembling a structure. The systems and method including micro pulsing a structure along a track in a process direction by less than a length of the structure. The structure is indexed to one or more work stations by mating indexing features in a manufacturing excess of the structure to complementary features at the work stations. The work stations would the perform work on the structure at the work stations while the structure is indexed to the work stations. Iteratively repeating the micro pulsing and indexing and working upon the structure until it is ready to advance to the next assembly process.

Systems and methods are provided for assembling a wing. Methods include suspending an upper wing panel of an aircraft beneath a shuttle, translating a rib to a position it, and placing the rib into contact with, then affixing the rib to, the upper wing panel, while suspended. Some methods include installing ribs and spars to the upper wing panel, and joining a lower wing panel to the ribs and spars, while the upper wing panel is suspended. Some methods involve joining ribs to spars (e.g., all, or some) to produce a support structure that is then affixed to the upper wing panel. Systems include a shuttle that suspends an upper wing panel, and a cart that includes supports to hold a rib, a chassis to translate the rib to a position beneath the upper wing panel, and a lifting apparatus to lift the rib into contact with the upper wing panel.

Systems, methods, and apparatus are provided for assembling a wing. Methods include coupling a robot arm to a bracket on a rib held against a wing panel, and operating the coupled robot arm to install shims between the rib and wing panel. Some methods further include mounting (e.g. detachably) the bracket, such as by aligning it with indexing features at the rib. In some methods, the bracket enforces a contour to the rib. Systems include a carriage coupled to a rib, and a robot arm extending therefrom that is operable to perform work (e.g. inspection, installing shims and/or fasteners, etc.) at an interface between the rib and a wing panel. Apparatus includes a robot arm dimensioned for placement at an interface between a rib and a wing panel, with the robot arm including an end effector to perform work upon the interface (e.g. inspection, installing shims and/or fasteners, etc.).

Systems and methods are provided for assembling an aircraft. The method includes receiving an upper half barrel section of fuselage that is in a crown up orientation and installing a crown module into the upper half barrel section.

Systems and methods are provided for fabrication of frames for aircraft.

Systems and methods are provided for inspecting a structure. One embodiment is a method for inspecting a structure. The method includes advancing a structure along a track in a process direction, aligning a Non-Destructive Inspection (NDI) station at the track with an edge of the structure that was trimmed upstream of the cleaning station, imaging the edge via the Non-Destructive Inspection (NDI) station, characterizing the edge based on the imaging, and advancing the structure further in the process direction via the track.