Motion and orientation control for spacecraft on a high elliptic orbit

Аuthors

Obukhov V. A.^1*, Pokryshkin A. I.^*, Popov G. A.^2**, Yashina N. V.^3***

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
3. The «Generation» Research Center at the Moscow Aviation Institute,

*e-mail: riame@sokol.ru
**e-mail: riame4@sokol.ru
***e-mail: aet@mai.ru

Abstract

An electrical rocket propulsion system structure is proposed with rotating thrusters. The thrusters have star-like arrangement. They are located uniformly in the same plane while nominal directions of their thrusts cross the spacecraft inertia axis which is orthogonal to this plane. The suggested propulsion system structure allows to solve efficiently such problems as high elliptic orbit correction and spacecraft attitude control. The system ensures to enhance spacecraft energy efficiency by means of more comprehensive using of solar cell panel power and more saving consumption of fuel.