DOI: 10.14489/vkit.2015.09.pp.009-015

Козорез Д. А., Красильщиков М. Н., Кружков Д. М.
КОМПЬЮТЕРНОЕ МОДЕЛИРОВАНИЕ ПРОЦЕССА ДОВЫВЕДЕНИЯ КОСМИЧЕСКОГО АППАРАТА НА ГЕОСТАЦИОНАРНУЮ ОРБИТУ С ИСПОЛЬЗОВАНИЕМ СТАЦИОНАРНОГО ПЛАЗМЕННОГО ДВИГАТЕЛЯ
(с. 9-15)

Аннотация. Приведены функциональные схемы моделирования, диаграммы классов программного обеспечения для имитационного моделирования процесса довыведения космического аппарата на геостационарную орбиту. Дан анализ результатов моделирования, на основании которого формируются требования к бортовым аппаратным средствам автономной навигационной системы.

Ключевые слова:  навигация; неконтролируемые факторы; управление центром масс и ориентацией; стационарный плазменный двигатель; глобальные спутниковые системы; геостационарная орбита; моделирование.

Kozorez D. A., Krasilshchikov M. N., Kruzhkov D. M.
COMPUTER SIMULATION OF THE SPACECRAFT INSERTION PROCESS INTO GEOSTATIONARY ORBIT BY ELECTRIC PROPULSION SYSTEM
(pp. 9-15)

Abstract. The paper is dedicated to computer simulation process of the spacecraft insertion into geostationary orbit using electric propulsion system. The goal of the mentioned simulation is to compute the dependence between terminal insertion process both accuracy and duration and onboard navigation system hardware performances. Standard procedure for payload insertion into geostationary orbit includes booster utilization for transfer from intermediate orbit to terminal one. In this situation electric propulsion system utilization gives significant advantages from the point of view payload mass amount, being inserted into geostationary orbit. However, the additional scientific and technical problem arises, namely: it is necessary to create the onboard autonomous navigation system, which can be evaluate not only payload position and velocity components, but electric propulsion system thrust vector attitude relative to spacecraft body axis. The main complexity for the mentioned navigation problem solution consists in the following: the electric propulsion system control acceleration is comparable with result of natural uncontrollable factors (Earth, Sun and Moon gravity, solar pressure, etc.) influence. So, considering nonlinearity of utilized spacecraft motion mathematical models, as well as variety of different natural uncontrollable factors, only computer mathematical simulation can assist to receive representative preliminary results in order to define the requirements for navigation system onboard hardware. The paper contains the simplified diagram of simulation, software class diagrams as well as simulation results analysis, which allow creating the requirements for onboard navigation hardware.

Keywords: Navigation; Uncontrollable factors; Masscenter and attitude control; Electric propulsion system; GNSS-receiver; Geostationary orbit; Computer simulation.