Abstract: GH4141 has high high-temperature strength and good oxidation resistance, and is widely used in aviation fasteners. In order to study the upsetting process of a large-sized GH4141 high-temperature alloy twelve point bolt for aviation, the hot deformation behavior of GH4141 high-temperature alloy after homogenization treatment was studied through high-temperature compression experiments at deformation temperatures of 1 000～1 200 ℃ and strain rates of 0.01～0.1 s⁻¹, analyzed the rheological stress curves of materials under different deformation temperatures and strain rates, and imported the performance data of GH4141 high-temperature alloy obtained from high-temperature compression experiments into Deform-3D. Numerical simulation was conducted on the top upsetting process of GH4141 high-temperature alloy twelve point bolts,and the load time curve and equivalent stress field distribution during the forming process were analyzed The distribution of equivalent strain and the influence of different friction coefficients on the forming load were studied. Finally, the mold structure design,processing and process experiments were carried out based on the simulated process parameters. The research results indicate that when the strain rate remains constant, the higher thedeformation temperature, the lower the thermal deformation resistance of GH4141 high-temperature alloy. When the deformation temperature remains constant, the higher the strain rate, the lower the thermal deformation resistance of GH4141 high-temperature alloy. μ=0.12, the maximum load during the forming processis 3.56×10⁶ N, μ=0.3, the maximum load during the forming process is 3.56×10⁶ N, μ=0.5, the maximum load during the forming process is 4.11×10⁶ N. The GH4141 high-temperature alloy twelve point bolt forging obtained from the final process test is fully filled with no forging defects, which has certain guiding significance for the actual production of GH4141 high-temperature alloy bolts.