Trajectory optimization for small launchers using a genetic algorithm approach

In the past few years, an important increase in the small satellites market has been noticed by the space community. Following this boost on the small satellites business, the need for dedicated launch services arises and designing an efficient and competitive small launcher is a challenge. Together with an innovative design for a small launcher comes the need for the optimization of the trajectory. A trajectory optimization approach has a lot to bring in terms of launcher performances such as achievable payload mass or a higher altitude of the target orbit. This paper is focused on an in-house 3 degree-of-freedom (3DOF) tool for trajectory computation and optimization using a genetic algorithm approach. The cost function is built in such a way to maximize the payload mass of the launcher while achieving the target orbit. The tool is also used for performing sensitivity analyses considering structural mass uncertainties, that can play an important role in the design phase of the vehicle, in order to check their impact on the launcher’s performances.