A surrogate-model multidisciplinary design optimization methodology for trajectory optimization of a launch vehicle

Keramatinejad, Mahdi; Ali Mohamadi, Hamidreza; Karbasian, Mahdi; Atashgar, Karim

doi:10.22034/jast.2025.459169.1188

A surrogate-model multidisciplinary design optimization methodology for trajectory optimization of a launch vehicle

Document Type : Original Article

Authors

mahdi keramatinejad ¹

Hamidreza Ali Mohamadi ²

mahdi karbasian ³

karim Atashgar ³

¹ Faculty of Management & Industrial Engineering, Malek Ashtar University of Technology, Iran

² Aerospace Research Institute

³ Faculty of Management & Industrial Engineering, Malek Ashtar University of Technology, Iran

10.22034/jast.2025.459169.1188

Abstract

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.

Keywords

Launch Vehicle (LV)

design of experiment (DOE)

Trajectory Optimization

surrogate- model

response surface method (RSM

Subjects

Aerospace systems Design

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