On Attainability of Small Bodies by Use of the Solar Sail Spacecraft

Details On Attainability of Small Bodies by Use of the Solar Sail Spacecraft On Attainability of Small Bodies by Use of the Solar Sail Spacecraft

Jan 1999

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1999adspr..24.1185p&link_type=abstract

Advances in Space Research, Volume 24, Issue 9, p. 1185-1185.

Computer Science

Scientific paper

The unrotating self-opening solar sail spacecraft with the design briefly explained here have been assume to use for the multitarget programs of small bodies exploration. The calculations of the sail mass taking into account the sail stability show, that the modern technology permits to reduce the sail mass to 15-30 % of the complete spacecraft mass which is supposed to be about 100 kg. The spacecraft with a solar sail can make the survey of asteroids by flying close to its surface and can make the distant capture of the small body ground sample at close contact. The technique and results of the calculations of the minimal flyby time transfer trajectories of the spacecraft with solar sail to the asteroids or comets are presented. The calculations are proceed for the period 1998-2001 and for the starts of a solar sail vehicle from the circular heliocentric orbits of the Earth, Mars or small planet Vesta. It is shown that for any arrival data always exist the asteroid (or comet) that can be achieved during 5-10 months flyby time. The solar sail lightness number (the ratio of the maximal thrust to the solar attraction) α = 0.083 was chosen and more 6300 well known asteroids were examined. The influence of this parameter α to the transfer duration is considered also

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