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Global Optimization Approach for the Ascent Problem of Multi-stage Launchers

O. Bokanowski (), E. Bourgeois (), A. Désilles () and H. Zidani ()
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O. Bokanowski: University Paris Diderot, Lab. J.-L. Lions
E. Bourgeois: CNES Launcher Directorate
A. Désilles: Unité de Mathématiques Appliquées (UMA), Ensta ParisTech
H. Zidani: Unité de Mathématiques Appliquées (UMA), Ensta ParisTech

A chapter in Modeling, Simulation and Optimization of Complex Processes HPSC 2018, 2021, pp 1-42 from Springer

Abstract: Abstract This paper deals with a trajectory optimization problem for a three-stage launcher with the aim to minimize the consumption of propellant needed to steer the launcher from the Earth to the GEO (geostationary orbit). Here we use a global optimization procedure based on Hamilton-Jacobi-Bellman approach and consider a complete model including the transfer from a GTO (geostationary transfer orbit) to the GEO. This model leads to an optimal control problem involving also some optimization parameters that appear in the flight phases. First, an adequate formulation of the control problem is introduced. Then, we discuss some theoretical results related to the value function and to the reconstruction of an optimal trajectory. Numerical simulations are given to show the relevance of the global optimization approach. This work has been undertaken in the frame of CNES Launchers’ Research and Technology program.

Keywords: Hamilton-Jacobi Bellman approach; Global optimum; State constraints; Numerical analysis; Propellant optimization for space launcher problem (search for similar items in EconPapers)
Date: 2021
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Persistent link: https://EconPapers.repec.org/RePEc:spr:sprchp:978-3-030-55240-4_1

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DOI: 10.1007/978-3-030-55240-4_1

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