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This study completes a previous one 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 explicitlydoi:10.13009/eucass2017-71 fatcat:vksctkbvxvdcbarvargxhimcfe