• Optimization
• Marte
• Mars
• Dimensionamento
• Design
• Ottimizzazione

This thesis presents a preliminary study of an Earth-Mars mission. The main goal is to develop a transfer module compatible with the VEGA E launch system and able to carry a payload of at least 300 kg, starting from 2024. To this end, the first step of the study is the analysis and optimization of the interplanetary transfer, starting from a fixed reference parking orbit and considering all the possible strategies to reduce the transfer ∆V , as deep space maneuvers and flybys. After that, the total ∆V budget is evaluated considering raising, errors and the launch itself. In this phase, also a variable parking orbit is introduced in order to find the optimal choice for each ascent- transfer combination and complete the optimization process of the total ∆V . With the introduction of mass data, configuration and a parametrization of the dependent variables with the propellant mass, the maximum payload solutions are found for each year in terms of parking orbit, tanks requirements and ∆V. All the optimizations processes are implemented in Matlab using both a genetic algorithm and a parametric formulation. Finally, with a trade-off from all those solutions it is possible to choose a nominal configuration for the vehicle and analyze the performance of this transfer module in the desired range.