Surrogate Finite-Element Modelling for Launch Vehicle Multidisciplinary Optimization

Abstract

A multi-disciplinary optimization approach is crucial to reduce development time and costs for new launch vehicle configurations, especially in light of the imminent increase in demand for launch services. This paper aims to present a methodology for obtaining a launch vehicle structural model that can be used for multidisciplinary design optimization through the use of genetic algorithms and radial basis functions. Specifically, a finite-element model generator is developed and used to create a solid rocket-based launch vehicle model, whose input parameters (geometry and loads) are affected by the selected payload and mission. To determine the critical load cases needed to size the structural components, the trajectory profile from takeoff to orbit insertion is of paramount importance. The use of surrogate models enhances the process of identifying the optimal design by enabling reductions in the running time of the optimization procedure, making the finite-element analysis suited for conceptual studies.