TY - JOUR

T1 - Orbital motion control of an electrically charged spacecraft

AU - Клюшин, Максим Александрович

AU - Тихонов, Алексей Александрович

AU - Giri, Dipak Kumar

N1 - Export Date: 18 November 2024 CODEN: AASTC Сведения о финансировании: Russian Science Foundation, RSF, 24-41-02031 Сведения о финансировании: Russian Science Foundation, RSF Текст о финансировании 1: The work is supported by the Russian Science Foundation (grant No. 24-41-02031 , https://rscf.ru/project/24-41-02031/ ).

PY - 2025/1/1

Y1 - 2025/1/1

N2 - In this paper, the orbital motion of an electrically charged spacecraft in the gravitational and magnetic fields of the Earth is investigated. The “direct magnetic dipole” is considered as a model of the geomagnetic field. The nonlinear non-autonomous system of differential equations of motion of the spacecraft center of mass in the Cartesian and spherical coordinate systems is derived. The analytical study of the influence of the Lorentz force on the orbital motion of a charged spacecraft is carried out. The approximate solution of the differential system is found. The results of numerical simulation of the spacecraft orbital motion based on the derived system of differential equations are presented. The analytical and numerical solutions are compared. The problem of stabilizing the spacecraft's center of mass in the orbital plane is considered. Feedback control methods based on the use of jet engines are proposed. The technical justification of the proposed control methods is carried out. As a result, stabilization of an electrically charged spacecraft in a small neighborhood of the plane of the initial orbit is achieved. The motion of a spacecraft with a variable electric charge is considered. Methods of controlling orbital motion due to low thrust as a result of the Lorentz force effect are proposed. © 2024 IAA

AB - In this paper, the orbital motion of an electrically charged spacecraft in the gravitational and magnetic fields of the Earth is investigated. The “direct magnetic dipole” is considered as a model of the geomagnetic field. The nonlinear non-autonomous system of differential equations of motion of the spacecraft center of mass in the Cartesian and spherical coordinate systems is derived. The analytical study of the influence of the Lorentz force on the orbital motion of a charged spacecraft is carried out. The approximate solution of the differential system is found. The results of numerical simulation of the spacecraft orbital motion based on the derived system of differential equations are presented. The analytical and numerical solutions are compared. The problem of stabilizing the spacecraft's center of mass in the orbital plane is considered. Feedback control methods based on the use of jet engines are proposed. The technical justification of the proposed control methods is carried out. As a result, stabilization of an electrically charged spacecraft in a small neighborhood of the plane of the initial orbit is achieved. The motion of a spacecraft with a variable electric charge is considered. Methods of controlling orbital motion due to low thrust as a result of the Lorentz force effect are proposed. © 2024 IAA

KW - Geomagnetic field

KW - Lorentz force

KW - Orbital motion control

KW - Spacecraft

KW - Stabilization

KW - Variable electrical charge

KW - Feedback control

KW - Negative ions

KW - Orbits

KW - Positive ions

KW - Surface discharges

KW - Centers-of-mass

KW - Charged spacecraft

KW - Electrical charges

KW - Geomagnetic fields

KW - Gravitational fields

KW - Lorentz

KW - Orbital motions

KW - System of differential equations

UR - https://www.mendeley.com/catalogue/ceb07686-e176-3114-b223-fa819baae1f1/

U2 - 10.1016/j.actaastro.2024.10.043

DO - 10.1016/j.actaastro.2024.10.043

M3 - Article

VL - 226

SP - 626

EP - 636

JO - Acta Astronautica

JF - Acta Astronautica

SN - 0094-5765

ER -