Abstract: A method and apparatus for shaping fuselage sections. A first fuselage section is held in a holding structure in a cradle in a cradle system. Force are applied to the first fuselage section with an actuator system to a portion of the first fuselage section such that a first current shape of the first fuselage section changes towards a first desired shape for the first fuselage section to join the first the fuselage section to a second fuselage section.

Abstract: A method and apparatus for processing fuselage sections. The apparatus comprises a cradle system, a metrology system, and a controller. The cradle system holds a first fuselage section and applies forces to the first fuselage section to change a current shape of the first fuselage section. The metrology system makes measurements of the current shape of the first fuselage section. The controller receives the measurements from the metrology system, identifies the forces needed to change the current shape of the first fuselage section towards a desired shape for connecting the first fuselage section to a second fuselage section, and sends commands to the cradle system to apply the forces to change the current shape of the first fuselage section towards the desired shape.

Abstract: Methods and an apparatus for processing fuselage sections. Measurements of a first fuselage section are generated using a scanning system. The scanning system includes a first scanner and a second scanner. The first scanner generates measurements of a first portion of the first fuselage section and the second scanner generates measurements of a second portion of the first fuselage section. The first fuselage section is held in a cradle system. The measurements of the first portion of the first fuselage section are combined with the measurements of the second portion of the first fuselage section to generate an ensemble of measurements of the first fuselage section. Using the cradle system, one or more of the first fuselage section or a second fuselage section are shaped based on the ensemble of measurements. Using the cradle system, the first fuselage section is joined with the second fuselage section.

Abstract: Methods and an apparatus for processing fuselage sections. Measurements of a first fuselage section are generated using a scanning system. The scanning system includes a first scanner and a second scanner. The first scanner generates measurements of a first portion of the first fuselage section and the second scanner generates measurements of a second portion of the first fuselage section. The first fuselage section is held in a cradle system. The measurements of the first portion of the first fuselage section are combined with the measurements of the second portion of the first fuselage section to generate an ensemble of measurements of the first fuselage section. Using the cradle system, one or more of the first fuselage section or a second fuselage section are shaped based on the ensemble of measurements. Using the cradle system, the first fuselage section is joined with the second fuselage section.

Abstract: A method and apparatus for processing fuselage sections. A scanning system is positioned between a first fuselage section held in a first cradle and a second fuselage section held in a second cradle. A group of beams of light is transmitted from the scanning system to targets on a first interior surface of the first fuselage section and a second interior surface of the second fuselage section. A reflected light is detected from a beam of light. Measurements of the first fuselage section and the second fuselage section are generated from using the reflected light generated in response to the beam of light. The measurements enable shaping at least one of the first fuselage section and the second fuselage section for joining the first fuselage section to the second fuselage section.

Abstract: A method and apparatus for shaping fuselage sections. A first fuselage section is held in a holding structure in a cradle in a cradle system. Force are applied to the first fuselage section with an actuator system to a portion of the first fuselage section such that a first current shape of the first fuselage section changes towards a first desired shape for the first fuselage section to join the first the fuselage section to a second fuselage section.

Abstract: A method and apparatus for processing fuselage sections. The apparatus comprises a cradle system, a metrology system, and a controller. The cradle system holds a first fuselage section and applies forces to the first fuselage section to change a current shape of the first fuselage section. The metrology system makes measurements of the current shape of the first fuselage section. The controller receives the measurements from the metrology system, identifies the forces needed to change the current shape of the first fuselage section towards a desired shape for connecting the first fuselage section to a second fuselage section, and sends commands to the cradle system to apply the forces to change the current shape of the first fuselage section towards the desired shape.

Abstract: A method and apparatus for processing fuselage sections. A scanning system is positioned between a first fuselage section held in a first cradle and a second fuselage section held in a second cradle. A group of beams of light is transmitted from the scanning system to targets on a first interior surface of the first fuselage section and a second interior surface of the second fuselage section. A reflected light is detected from a beam of light. Measurements of the first fuselage section and the second fuselage section are generated from using the reflected light generated in response to the beam of light. The measurements enable shaping at least one of the first fuselage section and the second fuselage section for joining the first fuselage section to the second fuselage section.

Abstract: Illustrative computer-executable methods, systems, and computer software program products predict cruise orientation of an as-built airplane. In illustrative embodiments, nominal orientation of an as-built airplane is input. Deviation from the nominal orientation of the as-built airplane is automatically computed, and the computed deviation from the nominal orientation of the as-built airplane is applied to the nominal orientation of the as-built airplane.

Abstract: Illustrative computer-executable methods, systems, and computer software program products predict cruise orientation of an as-built airplane. In illustrative embodiments, nominal orientation of an as-built airplane is input. Deviation from the nominal orientation of the as-built airplane is automatically computed, and the computed deviation from the nominal orientation of the as-built airplane is applied to the nominal orientation of the as-built airplane.