Nullifying feasibility of slow gravitational perturbation effect on the formation flying configuration

Аuthors

Zaramenskikh I. E.^1*, Ovchinnikov M. Y.^2**, Ritus I. V.^3***

1. Moscow Institute of Physics and Technology (National Research University), 9, Institutskiy per., Dolgoprudny, Moscow region, 141701, Russia
2. Keldysh Institute of Applied Mathematics (Russian Academy of Sciences), 4, Miusskaya sq., Moscow, 125047, Russia
3. Institute for Mathematical Modelling RAS (IMM RAS), 4A, Miusskaya square, 125047, Moscow

*e-mail: flice@mail.ru
**e-mail: ovchinni@keldysh.ru
***e-mail: ritus@imamod.ru

Abstract

In order to keep Formation Flying it is necessary to eliminate the secular drift in relative motion. With an allowance for nonspherical Earth if the satellites have different orbits there are the secular drifts in longitude of ascending node and in argument of perigee. In the present paper the ability to nullify the secular drifts for two satellites in perturbed gravitational field is performed. The deputy satellite has low thrust propulsion and passive magnetic attitude control system.

Keywords:

Small satellite; passive magnetic attitude control system; Formation Flying; relative position control

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