Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, a method for repetitively manufacturing aircraft comprises fractionally pulsing a constituent part down an assembly line by periodically advancing the constituent part down the assembly line by less than a length of the constituent part. The periodic advancing may include advancing the aircraft component by a pulse length that is less than the length of the aircraft component, stopping movement of the aircraft component for a duration and performing work on the aircraft component, and then advancing the aircraft component by the pulse length again. In another example, a method comprises determining a fractional pulse length to fractionally pulse one or more constituent parts of an aircraft based on one or more of a minimum workstation length of one or more assembly line workstations and a minimum section length of one or more work processes to be performed.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, an aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: An aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, an aircraft manufacturing system for repetitively manufacturing aircraft comprises a first manufacturing zone configured to repetitively manufacture first aircraft subassemblies, a second manufacturing zone configured to repetitively manufacture second aircraft subassemblies, and a third manufacturing zone configured to receive the first aircraft subassemblies from the first manufacturing zone, to receive the second aircraft subassemblies from the second manufacturing zone, and to repetitively assemble the first aircraft subassemblies and the second aircraft subassemblies into the aircraft.

Abstract: Systems and methods for manufacturing aircraft are disclosed. For example, a method for repetitively manufacturing aircraft comprises fractionally pulsing a constituent part down an assembly line by periodically advancing the constituent part down the assembly line by less than a length of the constituent part. The periodic advancing may include advancing the aircraft component by a pulse length that is less than the length of the aircraft component, stopping movement of the aircraft component for a duration and performing work on the aircraft component, and then advancing the aircraft component by the pulse length again. In another example, a method comprises determining a fractional pulse length to fractionally pulse one or more constituent parts of an aircraft based on one or more of a minimum workstation length of one or more assembly line workstations and a minimum section length of one or more work processes to be performed.

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 is provided of fabricating a composite stiffener having a curved web and at least one curved flange. A substantially straight length of unidirectional prepreg tape is placed on a carrier. The at least one curved flange is formed by using the carrier to steer a first portion of the tape onto a first curved tool surface. The curved web is formed by using the carrier to form a second portion of the tape onto a second curved tool surface.

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.