HJB approach for a multi-boost launcher trajectory optimization problem**This work is partially supported by Centre National d’Etudes Spa-tiales (CNES), under the grant RT-CR-430-1304-CNES, by iCODE Institute project funded by the IDEX Paris-Saclay, ANR-11-IDEX-0003-02, and by DGA under the grant DGA-ENSTA-06-60-037
| Autor: | Hasnaa Zidani, Anna Desilles, Olivier Bokanowski, Eric Bourgeois |
|---|---|
| Rok vydání: | 2016 |
| Předmět: |
0209 industrial biotechnology
Mathematical optimization 021103 operations research Optimization problem Payload Astrophysics::Instrumentation and Methods for Astrophysics 0211 other engineering and technologies Hamilton–Jacobi–Bellman equation Geosynchronous orbit Context (language use) 02 engineering and technology Trajectory optimization Optimal control 020901 industrial engineering & automation Control and Systems Engineering Control theory Physics::Space Physics Astrophysics::Earth and Planetary Astrophysics Orbit (control theory) Mathematics |
| Zdroj: | IFAC-PapersOnLine. 49:456-461 |
| ISSN: | 2405-8963 |
| DOI: | 10.1016/j.ifacol.2016.09.078 |
| Popis: | 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. |
| Databáze: | OpenAIRE |
| Externí odkaz: |
|