Multi-point forming method of aluminum alloy aircraft integral wall panel

Abstract

The invention discloses a multi-point forming method for a whole aluminum alloy wall plate of an aircraft. The multi-point forming method comprises the following steps of arranging the whole aluminum alloy wall plate with ribs between an upper multi-point die and a lower multi-point die of a quick reconstructing die surface, filling a filling material between the ribs, arranging an elastic cushion between the wall plate and the multi-point die, and gradually forming a whole aluminum alloy wall plate part with ribs by a die pressing method along a controllable deformation path. The multi-point forming method has the advantages that by utilizing the quick and adjustable characteristic of the reconstructing multi-point die surface, the wall plate parts with different geometric shapes and double curvatures can be processed by one set of equipment; compared with the traditional rolling and bending forming method and the pressing and bending forming method, the stress of the wall plate is uniform, and the forming quality can be guaranteed; compared with the shot peen forming method and the aging forming method, the deformation amount is large, and the forming efficiency is high; the method can be used for forming the whole aircraft wall plate with different rib structures and the double curvatures, the problems of large size and high rib in the whole wall plate forming process are solved, and the method can be applied to the manufacturing of other large ribbed curvature parts of aircrafts, rockets and the like.

Description

technical field [0001] The invention belongs to the field of metal plastic processing, in particular to a multi-point forming method for an aluminum alloy aircraft integral wall plate. Background technique [0002] In the field of aircraft manufacturing, aluminum alloy integral panels are increasingly widely used due to their outstanding advantages such as high structural efficiency, light weight, good rigidity, and long fatigue life. One of the challenges in siding, especially large double-curvature siding parts with varying siding rib heights and discontinuous changes in skin thickness. The traditional processing methods of aircraft integral wall panels include progressive press bending, roll bending, shot peening and aging creep forming, etc. Press-bending forming and roll-bending forming are partial forming, with low efficiency, difficult calculation of deformation path and reduction amount, aging creep forming requires large heating devices and molds, and shot-peening ...

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Problems solved by technology

[0003] The present invention provides a double-curvature aircraft integral panel forming that can not only be used for different rib structures, solve the technical problems in the manufacture of large aircraft, but also can be popularized and applied to the manufacture of other large ribbed curved surface parts such as spacecraft and rockets. A multi-point forming method for an aluminum alloy aircraft integral wall panel, which overcomes the above-mentioned shortcomings of the existing aluminum alloy aircraft integral panel forming method

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