Trajectories of spacecraft with electro-rocket engine for missions to the Main Belt asteroids Vesta, Fortuna and Mars’ satellite Phobos are investigated. The goal of missions – delivering of ground samples to the Earth. For Phobos mission analysis of trajectories is done for a big range of start/finish dates. The payload mass delivered to Phobos is estimated. The difference in payload mass for two models of low thrust: with variable (i.e. “ideal”) and constant jet velocity is considered. The usage of ideal model for calculation and analysis of trajectories is proved.

interplanetary flight, low thrust, Phobos, asteroid, ground sample

Theoretical and applied problems of mechanics