Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
5003096 | IFAC-PapersOnLine | 2016 | 6 Pages |
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.
Related Topics
Physical Sciences and Engineering
Engineering
Computational Mechanics
Authors
Olivier Bokanowsky, Eric Bourgeois, Anna Désilles, Hasnaa Zidani,