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The paper considers the problem of the optimal thrusters arrangement aboard a geostationary spacecraft. It is necessary to simultaneously ensure orbit correction and reaction wheels desaturation. A formalization for thrusters optimal arrangement problem is proposed. Examples of the minimal thrusters arrangement are given, taking into account the given limitations and requirements both in the case of regular operation and in the case of a possible failure of one of the thrusters. The influence of possible installation errors and the center of mass displacement is taken into account.

The paper describes the features and capabilities of the software to simulate the dynamics of near-Earth satellites. The software package allows the passive and controlled angular and orbital motion simulation of both single satellites and formations. The software also allows using the mathematical models of varying precision and complexity while performing the computations. The user-friendly GUI is designed in a way to prevent or minimize the possibility of inappropriate data entry. The package was created in C++ using Qt Framework, which ensures cross-platform functionality and compatibility.

The paper covers the attitude control and determination algorithms of the satellite equipped with two flexible appendages. One of the appendages is an antenna. It is connected to the satellite bus inelastically. The antenna itself is a major disturbance factor. Its dimensions by far exceed the dimensions of the bus, and the eigen frequencies of the antenna oscillations are low. The second appendage is a solar panel. The spacecraft moves on the geostationary orbit. The panel is connected via the one degree of freedom hinge. It rotates with the constant rate to provide continuous solar panel attitude towards the Sun. Attitude control and determination is achieved with the hardware installed on the satellite bus only. Moreover, the oscillations of the flexible elements have no natural damping. The control and determination algorithms are provided that stabilize the satellite bus and reduce the flexible appendages oscillations alongside. Special control algorithm is proposed that does not excite the oscillations and lowers the computational burden on the onboard computer. Different eigen forms are considered to represent the error in the appendages models.