Abstract
The article proposes the development of a method for the combined deorbiting large space debris objects from low Earth orbits, performed using an electric propulsion engine and an aerodynamic sailing device. Simulation modeling of the combined deorbiting was carried out for various combinations of parameters of deorbit scheme, such as the altitude of the initial orbit, the phase of solar activity at the moment of deorbiting start, the ballistic coefficient, the time of active operation of the control system, and the time of one battery charge. Analytical dependences of the minimum increment in the velocity of an electric propulsion system, gained in one impulse, and the minimum number of impulses on the parameters of the deorbiting scheme, necessary to ensure the withdrawal for 25 years, are determined. Sectors of the solar activity phase at the moment of the deorbiting start providing optimal energy costs for the withdrawal process, are identified. The results obtained are of practical interest for the problems of designing modern means of deorbiting large space objects from low Earth orbits at enterprises in the rocket and space industry.
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