A method and apparatus for manufacturing wings includes a fixture that holds wing panels for drilling and edge trimming by accurate numerically controlled machine tools using original numerical part definition records, utilizing spatial relationships between key features of detail parts or subassemb
A method and apparatus for manufacturing wings includes a fixture that holds wing panels for drilling and edge trimming by accurate numerically controlled machine tools using original numerical part definition records, utilizing spatial relationships between key features of detail parts or subassemblies as represented by coordination features machined into the parts and subassemblies, thereby making the parts and subassemblies intrinsically determinant of the dimensions and contour of the wing. Spars are attached to the wing panel using the coordination holes to locate the spars accurately on the panel in accordance with the original engineering design, and in-spar ribs are attached to rib posts on the spar using accurately drilled coordination holes in the ends of the rib and in the rib post. The wing contour is determined by the configuration of the spars and ribs rather than by any conventional hard tooling which determines the wing contour in conventional processes.
대표청구항▼
The invention claimed is: 1. A method of manufacturing a wing, comprising: positioning a wing panel on a fixture and holding said wing panel immobile on said fixture; accurately placing critical coordination features in said wing panel and in two wing spars using a numerically controlled machine to
The invention claimed is: 1. A method of manufacturing a wing, comprising: positioning a wing panel on a fixture and holding said wing panel immobile on said fixture; accurately placing critical coordination features in said wing panel and in two wing spars using a numerically controlled machine tool running on part programs incorporating digital wing product definition data from an engineering data authority, said critical coordination features being placed in said wing panel at locations having predetermined relationships with corresponding coordination features in said wing spars when said spars are accurately located in predetermined positions, spaced chord-wise from each other on said wing panel, specified by said digital wing product definition against said wing skin with said critical features in said spars and said wing skin positioned in said predetermined relation to each other; probing reference surfaces on said wing panel after positioning said wing panel on said fixture with a coordinate measuring system to obtain accurate position data for said wing panel on said fixture; normalizing said wing part program to coincide with said accurate position of said wing panel on said fixture; positioning said wing spars relative to said wing panel with said coordination features on said wing panel in registry with said coordination features on said wing spars and said wing spars thereby accurately located in said predetermined positions relative to said wing panel, as specified by said digital wing product definition; fastening said wing spars in fixed relation relative to said wing panel in said predetermined position. 2. A method of manufacturing a wing as defined in claim 1, further comprising: placing rib-to-spar critical coordination features in a plurality of wing ribs and in said spars using numerically controlled machine tools running on programs incorporating digital wing product definition from an engineering data authority, said ribs being accurately located in a predetermined position specified by said digital wing product definition relative to said wing spars when said rib-to-spar Critical features in said ribs and said wing spars are positioned In a predetermined relation to each other and fastening said wing ribs to said wing spars in said predetermined position. 3. A method of manufacturing a wing as defined in claim 2, further comprising: drilling a plurality of stringer-to-chord coordination holes in lower wing skin stringers attached to a lower wing skin and in a lower spar chord using a numerically controlled machine tool running on a program incorporating said digital wing product definition data from said engineering data authority, said lower wing skin being accurately located in a predetermined position specified by said digital wing product definition relative to said wing spars when said stringer-to-chord critical features in said ribs and said wing spars are positioned in a predetermined relation to each other; and fastening said wing stringers and said wing spars together in said predetermined position. 4. A method of manufacturing a wing as defined in claim 1, wherein: one spar is located on said wing panel at one point using a coordination hole common to said one spar and said wing panel and is located angularly on said wing panel using another reference coordination fixture; another spar is located on said wing panel by registry of another coordination hole common to said other spar and said wing panel, and is located angularly on said wing panel using a rib fastened between said spars to determine the spacing between said spars at a position along said spars remote from said coordination holes. 5. A method of manufacturing a wing as defined in claim 1, further comprising: placing rib-to-spar critical coordination features in a plurality of in-spar ribs and in said spars using numerically controlled machine tools running on programs incorporating digital wing product definition from an engineering data authority, said ribs being accurately located in a predetermined position specified by said digital wing product definition relative to said wing spars when said rib-to-spar critical features in said ribs and said wing spars are positioned in a predetermined relation to each other. 6. A method of assembling a wing in accordance with a digital engineering product definition of said wing and within tolerances specified In said definition, comprising: machining coordination features in major wing components, including a wing spar, a plurality of wing ribs, and a wing skin, using a numerically controlled machine tool running on a wing part program incorporating said digital wing product definition from an ultimate engineering data authority, said coordination features being accurately located in predetermined positions on said components specified by said digital wing product definition such that said components are positioned at positions specified by said digital wing product definition relative to each other when corresponding ones of said coordination features are aligned with each other: supporting a first wing skin in a horizontal orientation on a contoured fixture; and locating the other of said components relative to said first wing skin in a configuration determined by said coordination features to produce a wing in accordance with said digital engineering product definition of said wing and within tolerances specified in said definition. 7. A method of assembling a wing as defined in claim 6, further comprising: checking the accuracy of said machine tool by probing a monument of known dimensions and location with a probe carried by said machine tool to compare the predicted dimensions and location of said monument with the dimensions and location as actually measured by said machine tool. 8. A method of assembling a wing in accordance with a digital engineering product definition of said wing and within tolerances specified in said definition, comprising: machining coordination features in major wing components, including a wing spar, a plurality of wing ribs, and a wing skin, using a numerically controlled machine tool running on a wing part program incorporating said digital wing product definition from an ultimate engineering data authority, said coordination features being accurately located in predetermined positions on said components specified by said digital wing product definition such that said components are positioned at positions specified by said digital wing product definition relative to each other when corresponding ones of said coordination features are aligned with each other; supporting a first wing skin in a horizontal orientation on a contoured fixture; locating the other of said components relative to said first wing skin in a configuration determined by said coordination features to produce a wing in accordance with said digital engineering product definition of said wing and within tolerances specified in said definition; probing reference surfaces on said wing panel after positioning said wing skin on said fixture with a coordinate measuring system to obtain accurate position data for said wing panel on said fixture; and normalizing said wing part program to coincide with said accurate position of said wing panel on said fixture. 9. A method of assembling a wing as defined in claim 8, wherein: said reference features include said coordination features in said wing skin.
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