Abstract
The paper presents an algorithm of damping the initial angular rate of the SamSat-218D nanosatellite after its separation from the transporting-launching container. Three mutually orthogonal magnetic coils are used as actuators that provide damping of the initial angular rate on board the nanosatellite. The traditional B-dot algorithm is used as the damping algorithm. Two operating modes are possible for the B-dot algorithm: a continuous mode and a discrete one. As the continuous operating mode of the magnetic coils onboard the nanosatellite in orbital flight is inexpedient because of the necessity of measuring the Earth magnetic field intensity vector the discrete mode of operating of the algorithm of damping the initial angular velocities acquired by the nanosatellite after its separation from the transporting-launching container is analyzed. The results of the mathematical simulation during the analysis of choosing discretization intervals in the algorithm of damping the initial angular rate of the SamSat-218D nanosatellite are presented.
Highlights
В настоящее время в Самарском государственном аэрокосмическом университете ведётся работа по созданию и обеспечению запуска наноспутника стандарта CubeSat3U SamSat-218Д, предназначенного для демонстрации и лётных испытаний новых технологий
The paper presents an algorithm of damping the initial angular rate of the SamSat-218D nanosatellite after its separation from the transporting-launching container
As the continuous operating mode of the magnetic coils onboard the nanosatellite in orbital flight is inexpedient because of the necessity of measuring the Earth magnetic field intensity vector the discrete mode of operating of the algorithm of damping the initial angular velocities acquired by the nanosatellite after its separation from the transporting-launching container is analyzed
Summary
В настоящее время в Самарском государственном аэрокосмическом университете ведётся работа по созданию и обеспечению запуска наноспутника стандарта CubeSat3U SamSat-218Д, предназначенного для демонстрации и лётных испытаний новых технологий. Моделирование процесса демпфирования угловых скоростей наноспутника SAMSAT-218Д после выхода из транспортно-пускового контейнера // Вестник Самарского государственного аэрокосмического университета имени академика С.П. Эйлеровых углов γ a , αn , φn (угол прецессии – скоростной угол крена γ a , угол нутации – пространственный угол атаки αn , угол собственного вращения – аэродинамический угол крена φn ) с проекциями вектора угловых скоростей на связанные оси ω, x ω, y ω: z ωx = γ a cosαn + φ n + ω0b21, ωy = γ a sin φn sin αn + α n cosφn + ω0b22 , ωz = γ a cosφn sin αn − α n sin φn + ω0b23, где ω0 – орбитальная скорость наноспутника.
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