The invention discloses a manufacturing process of a large-size rotor shaft forging member having characteristics of high toughness and long service life and used for aerospace. The process steps comprise: raw material smelting, homogenization heating, material discharging, heating before forging, cogging, normalizing, coarse machining UT inspection, macrostructure detection and non-metallic inclusion detection, heating before forging, high temperature forging, cold deformation strengthening, cyclic heat treatment, sub-temperature quenching, cryogenic treatment, tempering, coarse machining flaw detection, and fine machining processing. According to the present invention, the technical indexes of the rotor shaft forging member produced by using the manufacturing process comprise that the tensile strength Rm (MPa) is more than or equal to 1250, the yield strength Rp0.2 (MPa) is more than or equal to 1100, the elongation A (%) is more than or equal to 10, the cross section shrinkage rateZ (%) is more than or equal to 45, the hardness HRC is more than or equal to 38, the impact energy (J) is more than or equal to 40, the fracture toughness K1C (MPa.m<1/2>) is more than or equal to 100, the grain size is not thicker than grade 5, and the rotary bending fatigue limit is not less than 600M Pa (Kt=1, R=-1).