On the Sample Return From Vesta by Low-Thrust Spacecraft

Details On the Sample Return From Vesta by Low-Thrust Spacecraft On the Sample Return From Vesta by Low-Thrust Spacecraft

Jan 1996

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1996eiaf.conf....1a&link_type=abstract

Workshop on Evolution of Igneous Asteroids: Focus on Vesta and the HED Meteorites, p. 1

Physics

Vesta Asteroid, Samples, Expeditions, Landing Modules, Electric Propulsion, Low Thrust, Soyuz Spacecraft

Scientific paper

It is well known that there would be tremendous scientific value in a sample-return mission to a main-belt asteroid such as Vesta. The sample return from Vesta by traditional high-thrust vehicles is impossible at the present time. Combining high- and low-thrust propulsion (electric propulsion with energy supply by solar arrays) would permit the solution of this problem. At first, the spacecraft would be boosted by the high-thrust engine to the hyperbolic velocity. The rendezvous with the asteroid would then be performed using the low-thrust engine. Flight time to asteroids such as Vesta or Fortune is 2-3 yr. The resulting payload would prove sufficient to solve the problem of the sample return (depending essentially on the parameters of the rocket and the space systems). After the rendezvous with the asteroid, in the case of return with the high-thrust engine, the landing module could land on the asteroid and then return to Earth. In the case of the low-thrust return, the distant sample grab is used. The hyperbolic velocity surplus of returning capsules can be diminished by means of an appropriate entrance into the Earth's atmosphere. If the Soyuz rocket is used, the payload mass near Vesta is equal to 700 kg (except EP and solar array mass). In this case the return with high thrust is possible. For a conversional rocket, there would be 400 kg of payload mass. This would allow landing of the scientific apparatus on the surface or to make a distant grab, with its low thrust returning to the Earth. The total expedition time depends on the combination of dates of the rendezvous with the asteroid and the return to Earth, and would be 4-5 yr for an asteroid such as Vesta. These mission variants suppose use of the new technology, in large part tested during flight, such as EP SPT, ESA-XX, "Super ULP" solar arrays, etc.

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