HJB approach for a multi-boost launcher trajectory optimization problem *

O Bokanowski; E Bourgeois; Anna Desilles; Hasnaa Zidani

HJB approach for a multi-boost launcher trajectory optimization problem *

O Bokanowski ^{1, 2} E Bourgeois ³ Anna Desilles ⁴ Hasnaa Zidani ⁴

1 UPD7 - Université Paris Diderot - Paris 7

2 LJLL - Laboratoire Jacques-Louis Lions

3 CNES - Centre National d'Etudes Spatiales - Direction Des Lanceurs.

4 OC - Optimisation et commande

Abstract : This work deals with an optimization problem for three-stage space launcher. The mission of the launcher is to put a given payload on the GEO orbit with the minimal propellant consumption. The considered flight sequence performs two boosts. The first one steers the launcher to a given GTO orbit. Then, after a ballistic flight, a second boost is used to perform the orbit transfer maneuver from the GTO to the GEO. We decompose the global optimization problem into two optimal control problems and we apply in this context the Hamilton-Jacobi-Bellman (HJB) approach together with a parameter optimization procedure.

Keywords : Hamilton-Jacobi approach reachability analysis Launcher problem optimal control problem Trajectory optimization

Document type :

Conference papers

Domain :

Mathematics [math] / Optimization and Control [math.OC]

Mathematics [math] / Numerical Analysis [math.NA]

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https://hal-ensta-paris.archives-ouvertes.fr//hal-01327671
Contributor : Hasnaa Zidani <>
Submitted on : Tuesday, June 7, 2016 - 12:54:32 AM
Last modification on : Wednesday, July 3, 2019 - 10:48:04 AM

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