In view of the complexity and difficulty of hypersonic vehicle analysis

a surrogate model was proposed to approximate the true model with complex disciplinary coupling in the process of performance analysis and optimization. According to the requirements of cruise mission

the objective of optimization was to optimize the static and dynamic performance and minimize the model difference. By means of sensitivity analysis

the surrogate model was established. The static and dynamic performance analysis of the surrogate model was carried out

and the results of the true model were compared to verify the accuracy of the surrogate model. It was found that the trend of the trimming characteristics of the two models was completely consistent

the difference of angle of attack was less than 3%

and the difference of elevator deflection angle was only about 20% when the lower angle of the front body was large. Based on the surrogate model and optimized performance index

the trimming performance optimization and gap metric optimization of the surrogate model’s shape parameters were compared with the optimization results of the true model and the optimization efficiency. It was found that the difference between the two results was less than 2%

but the optimization efficiency using surrogate model was improved by 456%. It was proved that the optimization based on the surrogate model can improve the optimization efficiency without compromise of the accuracy.