Low Thrust #1
- Simone Centuori (DEIMOS Space)
- Jeroen Van den Eynde (European Space Agency)
Computation of low thrust orbits in any given mission arc; optimal trajectories involving low thrust; low thrust transfer to LEO and GEO; comparison of electric and chemical propulsion trajectories; design and optimization of low thrust orbit transfers; low thrust station keeping; low thrust orbital transfers in the Two-Body problem;
The continuing development of solar-sail technology in combination with the rising interest in a mission to the Sun-Earth $L_5$ point for heliophysics and the search for Trojan asteroids, raises the question of using solar sailing as the primary propulsion method to enable such a mission. This paper therefore investigates a range of solar-sail transfers to the $L_5$ point, departing from...
We consider the problem of optimal low-thrust spacecraft geostationary orbit (GEO) insertion from initial circular orbit with 800 km height and 51.6 degrees inclination. Minimal time for electric propulsion insertion of considered nuclear powered heavy spacecraft  is about 117 days. Significant amount of this time (~90 days) the spacecraft spends in regions with harsh space radiation...