Launcher size optimization for a crewed Mars mission

Several proposals exist for human Mars mission architectures. An important question to resolve is determine the most appropriate size of launcher minimize costs, without compromising with risks, efficiency and future developments. Strategic choices are proposed. A fundamental choice direct surface option, one that greatly simplifies architecture avoids a complex costly LEO assembly giant vehicle. The second aerocapture orbit insertion. third EDL systems highest TRL in order risks at same time avoid possible cost overruns due qualification issues. Minimization achieved crew three. It shown an capacity 100–110 tonnes sufficient carry out using 5 heavy launchers. This result particular interest countries currently developing super launchers such capacity, like Starship SLS USA, Long March 9 China similar developments Russia. If Europe were also interested design launcher, it here could be based on Vulcain or Prometheus engines. As rather simple optimized high TRL, affordable. roadmap suggested preparatory missions exploration program.