As one of the missile thrust vector substitution control schemes， the gas rudder operates in a very complex high-temperature gas environment. It is difficult to accurately predict the surface force and thermal load of the gas rudder and predict its ablation. At home and abroad， relevant researches have been carried out on the aerodynamic characteristics and related thermal environment of gas rudders through experiments and numerical calculations， which proves the feasibility and accuracy of predicting and simulating gas rudder ablation by numerical method， and provides strong support for the subsequent design and optimization of gas rudder in engineering practice.