A method for forming an aluminum alloy rear bottom top cover component

Abstract

The invention provides a forming method of an aluminum alloy rear bottom top cover component. The aluminum alloy rear bottom top cover member has one or more convex holes, and the method includes the following steps: Step 1, blanking; Step 2, flat plate stamping; Step 3, solution treatment; Step 4, creep aging forming. The present invention uses a composite process combining stamping and creep aging forming to form the rear bottom top cover with convex holes, which not only solves the problems of low forming precision in the stamping process, but also overcomes the difficulty of the creep aging process for large curvature components. Insufficient molding. The invention has the advantages of high forming precision, good process repeatability, low residual stress, good dimensional stability and the like.

Description

technical field [0001] The invention belongs to the field of forming aluminum alloy top cover components, and in particular relates to a forming method of an aluminum alloy rear bottom top cover component. Background technique [0002] Creep aging forming technology is a technology that emerged to solve the high-performance and high-precision manufacturing problems of large and complex aerospace components. It has the advantages of high forming precision, low residual stress, and good process repeatability. This technology has been successfully applied In the manufacture of aerospace structural parts such as upper and lower skins of aircraft wings. [0003] The large top cover with convex holes, which has a large hole in the middle and small flanging holes on the periphery, is the main structural component of the aerospace launch vehicle fuel tank. The traditional forming method of this component is stamping, which not only has low forming accuracy , long processing cycle, ...

AI Technical Summary

Problems solved by technology

[0003] The large top cover with convex holes, which has a large hole in the middle and small flanging holes on the periphery, is the main structural component of the aerospace launch vehicle fuel tank. The traditional forming method of this component is stamping, which not only has low forming accuracy , long processing cycle, etc., and because the flanging process of the convex hole is located after the stamping process of the main body of the component, the flanging of the convex hole further affects the overall shape accuracy of the top cover component, and after the component is formed, there will be large internal Residual stress affects the final dimensional accuracy

[0004] The carrier rocket propellant tank includes structural parts such as the front bottom top cover and the rear bottom top cover. The curvature and chord height of the front bottom top cover are small. Realize the integrated molding of the front bottom and top cover, and for the rear bottom and top cover, the section line along the radial direction is formed by the connection of two elliptic curves, the curvature change and the chord height are large, and the creep aging molding is simply applied When the bottom and top cover are formed by technology, the component still cannot be deformed to the predetermined shape under the action of external force, and it is difficult for the component to meet the surface accuracy requirements after unloading the external force and rebound behavior

[0005] In addition, the mold is the tooling required for creep aging molding. In the existing creep aging mold equipment technology, a set of molds can only form components with a certain shape and size, and cannot realize the production of components with various specifications.

Images