Metal working – Means to assemble or disassemble – With signal – scale – illuminator – or optical viewer
Reexamination Certificate
2001-07-31
2002-11-19
Hughes, S. Thomas (Department: 3726)
Metal working
Means to assemble or disassemble
With signal, scale, illuminator, or optical viewer
C029S714000, C029S281100, C029S281000, C029S897200, C029S407100, C029S559000
Reexamination Certificate
active
06481096
ABSTRACT:
This application is based on and claims the priority under 35 U.S.C. §119 of German Patent Application 199 29 471.2, filed on Jun. 26, 1999, the entire disclosure of which is incorporated herein by reference.
FIELD OF THE INVENTION
The invention relates to an apparatus for producing large three-dimensional structural components such as an aircraft fuselage or the like having an elongated barrel-shaped configuration or an oval or circular cross-section.
BACKGROUND INFORMATION
So-called large volume or jumbo aircraft have fuselages assembled from shell sections, preferably shell sections reinforced by load supporting elements such as stringers and spars or ribs. One or more plate-shaped floor grids are mounted inside such large scale fuselages. The floor grids extend longitudinally inside the fuselage and from one side wall to the opposite side wall.
German Patent Publication DE 34 38 584 A1 discloses an apparatus for the manufacture of an aircraft fuselage, whereby large surface area, curved structural elements are assembled to form fuselage sections. These fuselage sections are then interconnected by an automatically operating orbital riveting machine and by manual labor to form fuselage components. The riveting takes place along so-called cross-seams, whereby the automatic orbital riveting machine travels along these cross-seams guided by a machine guide rail extending as a ring around the aircraft body or fuselage. The entire orbital riveting machine or system is mounted on a carriage that can travel along or rather in parallel to the longitudinal aircraft axis also referred to as the X-axis.
In the manufacture of aircraft fuselages, it is further known to assemble subassemblies in rigid jigs that determine the geometry of the subassembly. Such rigid jigs operate on the principle of orienting all subassemblies relative to a zero position in a rigid system. According to such a known system, the preassembled subassemblies are deposited in jigs and located relative to fixed system points with a so-called zero alignment. Such a zero alignment system has the disadvantages that the zero alignment can result in deviations, particularly along the interface between individually neighboring subassemblies. Such deviations can fall outside permissible tolerance ranges. Moreover, an adjusting of the individual subassemblies in order to assure the desired overall geometry of the aircraft fuselage is not possible. However, as long as the fuselage has a circular cross-section that is a cylindrical configuration, the use of the zero alignment or positioning is possible, whereby the subassemblies forming the lower body half are positioned and riveted first whereupon the cabin floor is inserted and connected with the spars or ribs of the lower body half. A so-called auxiliary carrier, also referred to as a presenting frame, holds the subassembly relative to the jig and tool system in position without any possibility of making compensating adjustments in the positioning. Thus, positional deviations of the floor structure relative to the fuselage body are possible, but cannot be corrected. Once the floor structure and the lower fuselage half are assembled, the upper side wall shell sections and upper shell sections are secured to the lower half, whereby the positioning is again performed by way of the above-mentioned zero alignment.
Efforts have been made for avoiding some of the above described drawbacks. Thus, U.S. Pat. No. 5,694,690 (Micale) describes a method for producing large scale aircraft bodies from a plurality of subassemblies, whereby the subassemblies or selected components of the subassemblies are provided with drilled coordination holes for an accurate positioning and assembly of the subassemblies. The coordination holes make sure that the elements of the subassembly are already accurately positioned relative to each other so that the resulting subassemblies become self-locating and thus intrinsically determine the final contour of the aircraft body independently of tooling. The drilling of the coordination holes is accomplished by a computer controlled precision robot which is directed to the drilling locations using a digital data set taken directly from original digital part definition records.
The above described methods leave room for improvement, especially with regard to reducing the assembly costs while still assuring the required accuracy in the configuration of the final large scale product, such as a fuselage for a jumbo aircraft.
OBJECTS OF THE INVENTION
In view of the above it is the aim of the invention to achieve the following objects singly or in combination:
to provide an assembly apparatus for producing large scale components such as jumbo aircraft bodies, whereby the assembly permits maintaining required, precise tolerance ranges without the need for high precision jigs and without drilling precisely positioned locating holes, while still assuring the accuracy of the three-dimensional large scale body;
to substantially increase the accessibility of tools to the assembly positions for performing most assembly work by robots, particularly the forming of longitudinal and cross-seams; and
to provide a system and apparatus which substantially is independent of the length of the large scale body so that substantially any required number of subassemblies can be jointed to each other without any additional matching adjustments so that an entire aircraft fuselage can be assembled.
SUMMARY OF THE INVENTION
The above objects have been achieved by performing the following steps with the aid of the apparatus according to the invention. A prefabricated longitudinal central assembly core is mounted at its ends, for example between support columns. Then, at least one floor grid is secured to the assembly core with the aid of clamping tools which mechanically fasten the floor grid to the core. Then, shell-shaped sections having a defined internal stiffness of their own are positioned by robot tools which are preferably computer controlled, sequentially around the central assembly core and then mechanically interconnected, for example by riveting. The positioning is performed in such a way that first side wall shell sections are positioned opposite one another and secured to the floor grid or grids by mechanical means. Thereafter, bottom shell sections and top shell sections are sequentially secured to the side shells and to one another to form individual body sections of the large body such as a fuselage which is then completed by interconnecting individual body sections to each other, for example by riveting along cross-seams.
It is an important advantage of the invention that the assembly of the prefabricated shell sections or subsections can take place within a precise tolerance range, whereby, for example an aircraft fuselage section can be assembled with the required precision, yet without jigs or locating holes. All prefabricated subsections are positioned relative to the central prefabricated core which itself is lightweight and has its own stiffness. The core forms part of the assembly station and can be reused. The prefabricated fuselage planking is mounted to the floor grid or to the floor grids held in precise positions by the central longitudinal assembly core. By first mounting the side wall shell sections to the floor grid or grids, it becomes possible to mount or assemble the bottom fuselage shell section and the top shell section to the side shells without any difficulties. In a preferred form, the side wall shells are first secured to the floor grid or grids in a row, whereupon the upper and lower shells can also be secured in respective rows to the row of side wall shells.
According to a preferred embodiment of the present method, the three-dimensional large structural component is assembled of at least two body sections which are interconnected by the above-mentioned cross-seam, whereby each individual body section is so formed that the lateral or side shells are positioned opposite each other and are mechanically connected to the floor grid or grids to form
Lehmker Joachim
Muehlnickel Karl-Heinz
Stoewer Udo-Henning
Vollmerhaus Ruediger
Airbus Deutschland GmbH
Fasse W. F.
Fasse W. G.
Hughes S. Thomas
Nguyen T.
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