Conceptual design of a fixed-wing UAV for Mars reconnaissance

As the exploration of Mars transitions from probes and rovers to the possibility of human missions, the focus must shift from slow scientific exploration to rapid and efficient reconnaissance. Current orbiters with limited coverage and slow rovers leave a critical gap in situational awareness and exploration capabilities for future astronauts. This thesis proposes the conceptual design and a feasibility analysis of a reusable, rocket-propelled Unmanned Aerial Vehicle (UAV) tailored for the thin atmosphere of Mars. Moreover, the study integrates aerodynamic sizing with numerical flight dynamics simulations based on real MOLA topographic data. The results validate the ef- fectiveness of the proposed design: simulation data show a liftoff distance of just 217 m and an operational range of 1500 km, while offering an endurance exceeding 4.5 hours. Ultimately, this work demonstrates that by using unconventional launch strategies and simple but reliable aerodynamic design, this aerial platform can effectively serve as a long-range scout, bridging the gap between orbit and ground to ensure the safety of future astronauts.