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Algorithm for extending the ballistic lifetime of a small Earth remote sensing spacecraft

O.D. Zhaldybina¹ , M.A. Ivanushkin^{1, 2} , M.R. Mordanov¹ , I.S. Tkachenko¹ , T.V. Starostina¹

¹ Samara National Research University, Samara, Russia
² Image Processing Systems Institute ― Branch of Federal Scientific Research Centre “Crystallography and Photonics” RAS, Samara, Russia

Accepted: 27.11.2025
DOI: 10.21046/2070-7401-2025-22-6-125-136

The paper deals with small Earth remote sensing spacecrafts. The purpose of the study is to analyze the influence of solar activity and residual atmosphere density on spacecrafts with an orbital altitude below 1000 km to increase their ballistic lifetime without a corrective propulsion system on board. Within the research, the factors influencing the evolution of the orbital parameters of the Aist-2D satellite are analyzed, and methods of controlling the orbital motion of a spacecraft without a corrective propulsion system are investigated. Dependencies of the perigee argument, orbital inclination, eccentricity, longitude of the ascending node, and orbital altitude of the satellite on time are plotted. Modeling of the orbital motion of Aist-2D at three orientation variants is carried out: solar orientation, orientation intended for imaging and communication with the ground station of information reception and transmission, mode with minimum midship area. A method for increasing the ballistic lifetime of satellites in low Earth orbit is proposed. The ballistic lifetime of a small spacecraft type Aist-2D can be extended by 135 days if the satellite operates according to the cyclogram proposed in this paper. An algorithm is developed to increase the ballistic lifetime of small spacecraft in low Earth orbit. The results of this research can be used in the development of small satellites.

Keywords: small spacecraft, Earth remote sensing, corrective propulsion system, residual atmosphere, solar activity

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