Heliocentric Trajectories of Solar Orbiter with Ion Propulsion

Аuthors

Loeb H. W.¹, Petukhov V. G.^2*, Popov G. A.^2**

1. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia
2. Research Institute of Applied Mechanics and Electrodynamics of Moscow Aviation Institute (RIAME MAI), Moscow, Russia

*e-mail: vgpetukhov@gmail.com
**e-mail: riame4@sokol.ru

Abstract

There are carried out analysis and optimization of low-thrust heliocentric trajectories of solar orbiter. There are analyzed and optimized both direct flight profile and flight profiles using multiply Earth and Venus gravity assists to decrease perihelion radius and consequence of Venus gravity assisted maneuvers separated by resonant orbits to increase inclination. It is analyzed the expediency of various orbital resonances using. It is demonstrated the feasibility of radiofrequency ion thrusters using to transfer into typical target heliocentric orbits.

Keywords:

optimal heliocentric trajectory; electric propulsion; ion thruster; gravity assisted maneuver

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