New improvements in the optimization of the launcher ascent trajectory through the HJB approach
Résumé
This study completes works presented at EUCASS 2015. We investigate the resolution of the launcher ascent trajectory problem by the so-called Hamilton-Jacobi-Bellman (HJB) approach. The method gives a global optimum without any initialization procedure; nevertheless, the computational cost increases quickly for high-dimension problems. To mitigate this, the payload mass was excluded from the parameters managed by the HJB equations. A new formulation is proposed to consider explicitly this parameter while limiting the computation time. An illustration is proposed on a heavy class launcher, for a GEO mission. This study has been performed in the frame of the CNES Launchers Research & Technology program.
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