Metal working – Method of mechanical manufacture – With testing or indicating
Reexamination Certificate
1998-05-11
2001-05-15
Echols, P. W. (Department: 3726)
Metal working
Method of mechanical manufacture
With testing or indicating
C029S407040, C029S407090, C029S466000, C029S709000, C029S720000
Reexamination Certificate
active
06230382
ABSTRACT:
TECHNICAL FIELD OF INVENTION
This invention relates in general to the field of aircraft manufacturing and, more particularly, to a system and method for assembling an aircraft.
BACKGROUND OF THE INVENTION
Constructing an aircraft begins with assembling detail parts into aircraft subassemblies. These aircraft subassemblies are later positioned adjacent one another for final assembly of the aircraft. Tooling fixtures are used throughout the assembly process to prevent detail parts and aircraft subassemblies from being located and assembled incorrectly. For example, one type of tooling fixture may include fixed position stops that the detail fitting or aircraft subassembly seats against in order to position the detail part or aircraft subassembly in three dimensions. After locating the detail part or aircraft subassembly with the tooling fixture, the detail part or aircraft subassembly may be drilled or attached to mating aircraft structure.
In addition to tooling fixtures, detail parts and aircraft subassemblies often include interface control points to properly locate mating aircraft structure. For example, one aircraft supplier may manufacture and supply the wings of the aircraft while another aircraft supplier may manufacture and supply the fuselage of the aircraft. The wing and fuselage subassemblies may contain interface control points to prevent mislocating or misaligning the wing subassemblies with the fuselage subassembly during final assembly of the aircraft.
Conventional tooling for aircraft assembly, however, suffer several disadvantages. For example, variations in tooling tolerances from one tooling fixture to another, and variations from one detail part or aircraft subassembly to another, prevent properly locating or aligning the aircraft subassemblies during final assembly of the aircraft. As a result, the assembled aircraft does not represent the aircraft as designed. Additionally, conventional tooling fixtures do not control or provide the ability to measure performance or other global characteristics of the aircraft during assembly. For example, variations between the left side of the aircraft and the right side of the aircraft will affect performance characteristics of the aircraft such as range and fuel consumption.
SUMMARY OF THE INVENTION
Accordingly, a need has arisen for an improved aircraft assembly system and method that provides increased control of performance characteristics of the aircraft during assembly. The present invention provides an improved aircraft assembly method and system that addresses shortcomings of prior aircraft assembly methods and systems.
According to one embodiment of the invention, a method for assembling an aircraft comprises: determining a three-dimensional representation of first and second aircraft structures using an optical positioning device; generating a predicted mate of the first and second aircraft structures based on the three-dimensional representation of the first and second aircraft structures using a processor; and generating an adjusted mate to enhance at least one performance characteristic of the aircraft using the processor.
According to another embodiment of the invention, a system for processing first and second aircraft structures of an aircraft comprises: an optical positioning system operable to generate a three-dimensional representation of the first and second aircraft structures; a processor operable to generate a predicted mate of the first and second aircraft structures; and an adjustment system operable to adjust the predicted mate to enhance at least one performance characteristic of the aircraft.
The invention provides several technical advantages. For example, in one embodiment of the invention, the system measures and controls performance characteristics of the aircraft during assembly of the aircraft such as roll moment and roll factor that result from wing sweep differential, wing dihedral angle differential, and wing twist differential between a left wing and a right wing. Therefore, the system enhances performance characteristics of the aircraft that affect aircraft performance, such as fuel consumption and range. In the same embodiment, the system measures and monitors interface control points of the aircraft and can adjust the interface control points to enhance the performance characteristics of the aircraft.
Other technical advantages will be readily apparent to one skilled in the art from the following figures, descriptions, and claims.
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Cunningham Clifton D.
Howard James J.
Koesters James P.
Leenhouts Michael A.
Mann, II Thomas H
Baker & Botts L.L.P.
Echols P. W.
Nguyen Trinh
Vought Aircraft Industries, Inc.
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