Abstract: A method and apparatus for positioning one component relative to another component. First metrology data may be identified for a first component and second metrology data may be identified for a second component. First locations of first features may be identified on the first component using the first metrology data. Second locations of second features on the second component may be identified using the second metrology data. A transformation may be computed based on the first locations identified and the second locations identified for use in modifying a movement plan of a robotic system for positioning the second component relative to the first component.

Abstract: A method for assembling an aircraft engine nacelle inlet lip includes automatically positioning, with a controller an automated workstation in two degrees of freedom to position an articulated assembly fixture docking station in at least two predetermined joining positions, and effecting, with the controller, an ordered assembly of at least a forward bulkhead joint, a forward bulkhead to lipskin joint, a chord member to lipskin joint, an inner barrel to lipskin joint, an aft bulkhead to lipskin joint and an outer barrel to lipskin joint through an interface between an automated assembly tool and at least one of a plurality of assembly fixtures interchangeably mounted on the docking station, where each assembly fixture corresponds to an assembly step of the aircraft engine nacelle inlet lip and at least one of the assembly fixtures is common to more than one assembly step of the aircraft engine nacelle inlet lip.

Abstract: An end effector is provided. The end effector comprises a housing, a movement system within the housing, an inspection system, a collar installation system, and a sealant application system. The housing has an operating window. The movement system comprises at least one of a rotation mechanism or a number of linear slides. The inspection system is associated with the movement system. The collar installation system is associated with the movement system. The sealant application system is associated with the movement system. Activating the movement system positions any of the inspection system, the collar installation system, or the sealant application system in an active position relative to the operating window.

Abstract: A system and method are provided to automate the assembly of a wing panel, such as utilized by commercial aircraft. In the context of a system, a tacking cell is provided that is configured to tack one or more stringers to a skin plank. The system also includes a riveting cell configured to receive a tacked plank from the tacking cell and to rivet the one or more stringers to the skin plank. The system also includes a splicing cell configured to receive a plurality of riveted planks from the riveting cell and to attach one or more splice stringers to the plurality of riveted planks. Further, the system includes a side of body cell configured to receive a spliced panel from the splicing cell and to attach a side of body chord thereto to produce a wing panel.

Abstract: A method and apparatus for preventing damage to a metal component that is susceptible to damage by electro-magnetic effects or reduce manufacturing assembly steps. An initial channel is formed through the metal component. The initial channel is defined by an inner surface. A bushing is placed into the initial channel, wherein the bushing has an outer surface and an inner channel. An interference fit is created between the outer surface of the bushing and the inner surface of the initial channel through the metal component. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to one that is suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component.

Abstract: Preventing damage to a metal component or reducing manufacturing assembly steps. An initial channel, defined by an inner surface, is formed through the metal component. A bushing is placed into the initial channel, the bushing having an outer surface and an inner channel. An interference fit is created between the outer surface and the inner surface. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to be suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component. A fastener is placed into the final channel to attach the metal component to a second component, wherein electrical magnetic effects occur between the fastener and the bushing.

Abstract: A method for assembling an aircraft engine nacelle inlet lip includes automatically positioning, with a controller an automated workstation in two degrees of freedom to position an articulated assembly fixture docking station in at least two predetermined joining positions, and effecting, with the controller, an ordered assembly of at least a forward bulkhead joint, a forward bulkhead to lipskin joint, a chord member to lipskin joint, an inner barrel to lipskin joint, an aft bulkhead to lipskin joint and an outer barrel to lipskin joint through an interface between an automated assembly tool and at least one of a plurality of assembly fixtures interchangeably mounted on the docking station, where each assembly fixture corresponds to an assembly step of the aircraft engine nacelle inlet lip and at least one of the assembly fixtures is common to more than one assembly step of the aircraft engine nacelle inlet lip.

Abstract: A method and apparatus for positioning one component relative to another component. First metrology data may be identified for a first component and second metrology data may be identified for a second component. First locations of first features may be identified on the first component using the first metrology data. Second locations of second features on the second component may be identified using the second metrology data. A transformation may be computed based on the first locations identified and the second locations identified for use in modifying a movement plan of a robotic system for positioning the second component relative to the first component.

Abstract: Preventing damage to a metal component or reducing manufacturing assembly steps. An initial channel, defined by an inner surface, is formed through the metal component. A bushing is placed into the initial channel, the bushing having an outer surface and an inner channel. An interference fit is created between the outer surface and the inner surface. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to be suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component. A fastener is placed into the final channel to attach the metal component to a second component, wherein electrical magnetic effects occur between the fastener and the bushing.

Abstract: A method and apparatus for preventing damage to a metal component that is susceptible to damage by electro-magnetic effects or reduce manufacturing assembly steps. An initial channel is formed through the metal component. The initial channel is defined by an inner surface. A bushing is placed into the initial channel, wherein the bushing has an outer surface and an inner channel. An interference fit is created between the outer surface of the bushing and the inner surface of the initial channel through the metal component. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to one that is suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component.

Abstract: A method and apparatus for preventing damage to a metal component that is susceptible to damage by electro-magnetic effects or reduce manufacturing assembly steps. An initial channel is formed through the metal component. The initial channel is defined by an inner surface. A bushing is placed into the initial channel, wherein the bushing has an outer surface and an inner channel. An interference fit is created between the outer surface of the bushing and the inner surface of the initial channel through the metal component. A final channel is formed through the bushing. In forming the final channel, material is removed from the bushing to increase a size of the inner channel to one that is suitable to receive a fastener and such that the inner surface of the metal component remains unexposed within the final channel. The final channel extends through a second component.