Document Type : Research Note

Authors

1 M.Sc. Student. Department of Aerospace Engineering, Khajeh Nasir Toosi University of echnology, , Tehran, Iran.

2 Associate Professor. Department of Aerospace Engineering, Khajeh Nasir Toosi University of Technology. Tehran, Iran.

Abstract

Considering increased demand for launching satellites into geostationary orbit and use of orbit-spectrum resources, preserving these resources is essential. Space bus is a communication satellite in GEO with orbital maneuvering mission to maintain the orbit-spectrum concession. In this paper, statistical design is performed with SDM method at the system level to derive system specifications for satellites with electric and chemical propulsions. Orbital analysis for this communication satellite with electric and chemical propulsions has also been performed separately and the results of the analysis and comparison of the use of these two types of propulsion systems for space bus are presented. Finally, the feasibility of this idea and its results are reported.

Keywords

Main Subjects

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