Abstract: Low cycle fatigue tests under different loading conditions （maximum stress of 330−540 MPa, stress amplitucle of 150−270 MPa） were conducted on aviation 2195 Al-Li alloy rolled plates. The effects of stress amplitude and average stress on cyclic strain response and fatigue life were analyzed. The fatigue life was predicted by using the Basquin model, Smith average stress correction model established by introducing mean stress in the Basquin model and Walker index model established by introducing mean stress sensitive degree in the correction model. The results show that under 270 MPa mean stress, with increasing stress amplitude, the strain amplitude of the alloy increased, and the fatigue life decrease. under 200 MPa stress amplitude, with increasing average stress, the ratchet strain of the alloy increased, and the fatigue life was shortened. Compared with mean stresses, the effect of stress amplitudes on fatigue life was more significant. The low cycle fatigue life prediction results of the Basquin model, Smith average stress correction model and Walker index model were all within the ±2 times error range, indicating a relatively high prediction accuracy. The prediction accuracy of the Smith average stress correction model and the Walker index model was similar, and the Basquin model had the lowest prediction accuracy. Introducing average stress correction could improve the prediction accuracy of the low cycle fatigue life of 2195 aluminum-lithium alloy, but this alloy was less sensitive to average stress.