surrogate modeling and optimization for the trajectory of a launch vehicle based on doe and rsm

The present paper tries to optimization of the ascent trajectory of two stages launch vehicle (lv) to achieve a low earth orbit (leo). to this end, the surrogate-model method by utilizing the design of experiment (doe) and the response surface method (rsm) were implemented as two effective means for optimizing. in this paper, the model-based optimization strategy aims to minimize the total mass of the first stage and ultimately reduce the costs of the launch vehicle. hence, d‐optimal structure has been used for the surrogate-model and 101 different experiments were carried out on the trajectory optimization. the analysis of variance (anova) results indicate that the implemented model is capable to predict the responses adequately within the limits of input parameters. therefore, the desirability function analysis for lv has been applied to optimize the total mass of the first stage. as a result, the capability of the proposed lv optimization method is 602 kg reduction in total mass. this value is significant in lv design.