Payload optimization for multi-stage launchers using HJB approach and application to a SSO mission

This paper deals with a payload optimization problem for three-stage space launcher. The mission of the launch vehicle is to put the payload on a sun-synchronous (SSO) orbit. The considered flight sequence includes two boosts. The first one steers the launcher to a transfer orbit. Then, after a ballistic flight, a second boost is used to perform the orbit transfer manoeuvre to inject the payload to the targeted SSO orbit. The optimization method presented here is based on the Hamilton-Jacobi-Bellman (HJB) approach for hybrid dynamical systems.