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

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.
Type de document :
Communication dans un congrès
20th IFAC Symposium on Automatic Control in Aerospace - ACA 2016, Aug 2016, Sherbrooke, Quebec, Canada. 2016, Proceeding IFAC
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https://hal-ensta.archives-ouvertes.fr/hal-01327671
Contributeur : Hasnaa Zidani <>
Soumis le : mardi 7 juin 2016 - 00:54:32
Dernière modification le : vendredi 17 février 2017 - 16:13:46

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  • HAL Id : hal-01327671, version 1

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O Bokanowski, E Bourgeois, Anna Desilles, Hasnaa Zidani. HJB approach for a multi-boost launcher trajectory optimization problem *. 20th IFAC Symposium on Automatic Control in Aerospace - ACA 2016, Aug 2016, Sherbrooke, Quebec, Canada. 2016, Proceeding IFAC. <hal-01327671>

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