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A technique for the complex analysis of the characteristics of orbits used for space vehicles for remote sensing of the Earth (RSE), taking into account their trajectory, is proposed. The results of mathematical modeling of the operating conditions of such devices are presented. The technique is tested taking into account the input parameters of the orbit of the BelKA spacecraft. The technique will be useful in choosing of complex orbital characteristics for RSE spacecraft at the stage of technical proposals.

About the authors

K V Mikhaylovskiy

Bauman Moscow State Technical University (National Research University)

Author for correspondence.

Mikhailovskiy Konstantin Valerievich, candidate of technical sciences, associate professor of the department “Rocket and space composite construction”. Bauman MSTU.

2-nd Baumanskaya str., 5/1, Moscow, Russia, 105005

M A Gorodetsky

Bauman Moscow State Technical University (National Research University)


Gorodetsky Mikhail Alekseevich, master student of the 2nd year of the department “Rocket and space composite construction”. Bauman MSTU.

2-nd Baumanskaya str., 5/1, Moscow, Russia, 105005


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Copyright (c) 2017 Mikhaylovskiy K.V., Gorodetsky M.A.

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