Ariane V Ascent Trajectory Optimization with a First-Stage Splash-Down Constraint

Abstract The paper describes a numerical approach for determining the optimal ascent trajectory into a geostationary transfer orbit of an ARIANE V type vehicle subject to a first stage splash-down constraint. The control function is angle of attack and for simplicity a planar ascent is considered. By parameterizing the control function and by introducing suitable time transformations the multi-stage system is formulated as a single stage system and solved numerically using sequential quadratic programming. It is concluded that this approach is efficient in terms of computer time and insensitive with respect to modelling weaknesses such as linear interpolation of aero- and thrust data.