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.

Surrogate finite-element modelling for launch vehicle multidisciplinary optimization / Mancini, L.; Lucchese, L.; Saltari, F.; Mastroddi, F.; Neri, A.. - (2022). (Intervento presentato al convegno AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 tenutosi a San Diego, California(USA)) [10.2514/6.2022-2443].

Surrogate finite-element modelling for launch vehicle multidisciplinary optimization

Mancini L.
Primo
;
Lucchese L.
Secondo
;
Saltari F.;Mastroddi F.
Penultimo
;
2022

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.
2022
AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022
surrogate model; fem; mdo; launch vehicle
04 Pubblicazione in atti di convegno::04b Atto di convegno in volume
Surrogate finite-element modelling for launch vehicle multidisciplinary optimization / Mancini, L.; Lucchese, L.; Saltari, F.; Mastroddi, F.; Neri, A.. - (2022). (Intervento presentato al convegno AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2022 tenutosi a San Diego, California(USA)) [10.2514/6.2022-2443].
File allegati a questo prodotto
Non ci sono file associati a questo prodotto.

I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.

Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11573/1617415
 Attenzione

Attenzione! I dati visualizzati non sono stati sottoposti a validazione da parte dell'ateneo

Citazioni
  • ???jsp.display-item.citation.pmc??? ND
  • Scopus 0
  • ???jsp.display-item.citation.isi??? ND
social impact