A simulation method of thermal vibration composite residual stress control of aluminum alloy ring

Abstract

The invention relates to the technical field of workpiece residual stress regulation, and discloses a simulation method for thermal vibration composite residual stress regulation of an aluminum alloy ring, comprising the following steps: S1. Refer to the national standard "GB / T 10120‑2013 Tensile Stress Relaxation Test for Metal Materials" Method" to carry out thermal stress relaxation test of aluminum alloy material; S2, to perform stress relaxation test curve fitting based on step S1; S3, to establish a numerical simulation model of aluminum alloy ring with initial stress; S4, to select an appropriate creep-type constitutive function , convert the stress relaxation constitutive curve equation of the aluminum alloy in step S2 to determine the material creep parameters of the aluminum alloy; S5, perform thermal aging simulation based on step S4; S6, based on the thermal aging numerical simulation result of step S5, perform vibration aging simulation, Realize the thermal-vibration composite numerical simulation of the ring; S7, analyze and check the thermal-vibration composite residual stress control effect of the numerical simulation model of the aluminum alloy ring. The results show that the internal residual stress of the aluminum alloy is homogenized after thermal-vibration composite aging.

Description

technical field [0001] The invention relates to the technical field of workpiece residual stress regulation, in particular to a simulation method for regulating and controlling the thermal vibration composite residual stress of an aluminum alloy ring. Background technique [0002] At present, the manufacturing technology for small and medium-sized (≤5m) ring forgings for launch vehicles has matured, and the overall aluminum alloy ring forgings have been used in the Long March 3 series, the Long March 4 series, and the Long March 5 series. With the launch of the development of heavy-duty launch vehicles with a diameter of 10 meters and a take-off mass of 3,000 tons in my country, the development of large ring forgings has become particularly urgent. However, with the increase in the specifications of ring forgings, the residual stress, shape and mechanical properties The consistency is poor, and the non-uniformity and discontinuity of the forming interface are more prominent, ...

AI Technical Summary

Problems solved by technology

With the development of heavy-duty launch vehicles with a diameter of 10 meters and a take-off mass of 3,000 tons in my country, the development of large-scale ring forgings has become particularly urgent. However, with the increase in the specifications of ring forgings, the residual stress, shape and mechanical properties The consistency is poor, and the inhomogeneity and discontinuity of the forming interface are more prominent, making it extremely difficult to form and form large-scale integral components

At present, there is still a large gap between my country's manufacturing capacity and demand for such specifications of light alloy components, and the manufacturing capacity cannot meet the requirements of the leapfrog development of heavy-duty rocket equipment.

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