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With interstellar mission concepts now being under study by various spaceagencies and institutions, a feasible and worthy interstellar precursor missionconcept will be key to the success of the long shot. Here we investigateinterstellar-bound trajectories of solar sails made of the ultra-light materialaerographite, known for its low density (0.18 kg m$^{-3}$) and highabsorptivity ($\mathcal{A}{\sim}1$), enabling remarkable solarirradiation-based acceleration. Payloads of up to 1 kg can swiftly traverse thesolar system and the regions beyond. Our simulations consider various launchscenarios from a polar orbit around the Earth with direct outbound trajectoriesand Sun diver launches with subsequent outward acceleration. Utilizing thepoliastro Python library, we calculate positions, velocities, and accelerationsfor a 1 kg spacecraft (including 720 g aerographite mass) with 10$^4$ m$^2$ ofcross-sectional area, corresponding to a 56 m radius. A direct outward Marstransfer yields 65 km s$^{-1}$ in 26 d. The inward Mars transfer, with a saildeployment at a minimum distance of 0.6 AU, achieves 118 km s$^{-1}$ in 126 d.Transfer times and velocities vary due to the Earth-Mars constellation andinitial injection trajectory. The direct interstellar trajectory peaks at 109km s$^{-1}$, reaching interstellar space in 5.3 yr defined by the heliopause at120 AU. Alternatively, the initial Sun dive to 0.6 AU provides 148 km s$^{-1}$of escape velocity, reaching the heliopause in 4.2 yr. Values differ based onthe minimum distance to the Sun. Presented concepts enable swift Mars flybysand interstellar space exploration. For delivery missions of sub-kg payloads,the deceleration remains a challenge.

Ultrafast transfer of low-mass payloads to Mars and beyond using aerographite solar sails