Abstract: A sample‐return mission to the Martian satellites using a con‐temporary solar sail for all post‐Earth‐escape propulsion is proposed. The 0.015 kg/m2 areal mass‐thickness sail unfurls after launch and injection onto a Mars‐bound Hohmann‐transfer ellipse. Structure and payload increase spacecraft areal mass thickness to 0.028 kg/m2. During the Mars encounter, the sail functions as a parachute in the outer atmosphere of Mars to accomplish aerocapture. On‐board thrusters or the sail maneuver the spacecraft into an orbit with periapsis near Mars and apoapsis near Phobos. The orbit is circularized for Phobos‐rendezvous; surface samples are collected. The sail then raises the orbit for Deimos‐rendezvous and sample collection. The sail next places the spacecraft on an Earth‐bound Hohmann‐transfer ellipse. During Earth encounter, the sail accomplishes Earth‐aerocapture or partially decelerates the sample container for entry into the Earth's atmosphere. Mission mass budget is about 218 grams and mission duration is less than five years.
Phobos/Deimos Sample Return via Solar Sail
Annals of the New York Academy of Sciences ; 1065 , 1 ; 429-440
01.12.2005
12 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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