Ultrafast transfer of low-mass payloads to Mars and beyond using aerographite solar sails. (arXiv:2308.16698v1 [astro-ph.IM])
<a href="http://arxiv.org/find/astro-ph/1/au:+Karlapp_J/0/1/0/all/0/1">Julius Karlapp</a> (1), <a href="http://arxiv.org/find/astro-ph/1/au:+Heller_R/0/1/0/all/0/1">René Heller</a> (2), <a href="http://arxiv.org/find/astro-ph/1/au:+Tajmar_M/0/1/0/all/0/1">Martin Tajmar</a> (1) ((1) Institute of Aerospace Engineering, Technische Universität Dresden (GER), (2) Max Planck Institute for Solar System Research, Göttingen (GER))
With interstellar mission concepts now being under study by various space
agencies and institutions, a feasible and worthy interstellar precursor mission
concept will be key to the success of the long shot. Here we investigate
interstellar-bound trajectories of solar sails made of the ultra-light material
aerographite, known for its low density (0.18 kg m$^{-3}$) and high
absorptivity ($mathcal{A}{sim}1$), enabling remarkable solar
irradiation-based acceleration. Payloads of up to 1 kg can swiftly traverse the
solar system and the regions beyond. Our simulations consider various launch
scenarios from a polar orbit around the Earth with direct outbound trajectories
and Sun diver launches with subsequent outward acceleration. Utilizing the
poliastro Python library, we calculate positions, velocities, and accelerations
for a 1 kg spacecraft (including 720 g aerographite mass) with 10$^4$ m$^2$ of
cross-sectional area, corresponding to a 56 m radius. A direct outward Mars
transfer yields 65 km s$^{-1}$ in 26 d. The inward Mars transfer, with a sail
deployment 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 and
initial injection trajectory. The direct interstellar trajectory peaks at 109
km s$^{-1}$, reaching interstellar space in 5.3 yr defined by the heliopause at
120 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 on
the minimum distance to the Sun. Presented concepts enable swift Mars flybys
and interstellar space exploration. For delivery missions of sub-kg payloads,
the deceleration remains a challenge.
With interstellar mission concepts now being under study by various space
agencies and institutions, a feasible and worthy interstellar precursor mission
concept will be key to the success of the long shot. Here we investigate
interstellar-bound trajectories of solar sails made of the ultra-light material
aerographite, known for its low density (0.18 kg m$^{-3}$) and high
absorptivity ($mathcal{A}{sim}1$), enabling remarkable solar
irradiation-based acceleration. Payloads of up to 1 kg can swiftly traverse the
solar system and the regions beyond. Our simulations consider various launch
scenarios from a polar orbit around the Earth with direct outbound trajectories
and Sun diver launches with subsequent outward acceleration. Utilizing the
poliastro Python library, we calculate positions, velocities, and accelerations
for a 1 kg spacecraft (including 720 g aerographite mass) with 10$^4$ m$^2$ of
cross-sectional area, corresponding to a 56 m radius. A direct outward Mars
transfer yields 65 km s$^{-1}$ in 26 d. The inward Mars transfer, with a sail
deployment 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 and
initial injection trajectory. The direct interstellar trajectory peaks at 109
km s$^{-1}$, reaching interstellar space in 5.3 yr defined by the heliopause at
120 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 on
the minimum distance to the Sun. Presented concepts enable swift Mars flybys
and interstellar space exploration. For delivery missions of sub-kg payloads,
the deceleration remains a challenge.
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