Trajectory Motion Study and Control Mode Optimization for the Space Objects Deorbiting

Aeronautical and Space-Rocket Engineering


Аuthors

Kul'kov V. M.*, Yegorov Y. G.**, Firsyuk S. O.***

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: vmk_1@mail.ru
**e-mail: yuyeg@mail.ru
***e-mail: iskramai@gmail.com

Abstract

This article addresses the pressing issue of the safety ensuring of space activities due to the near-Earth space littering with space debris (SD).
To rectify the problem of the SD disposal, it is necessary to elaborate safe and effective methods for closing-in with the SD, its capturing, and orbital transportation. The task of the SD orbital transportation after its capturing is a new challenge, which solution will require development of new models and algorithms for the space objects (SO) motion control and methods for computing their trajectory.
The article examines the trajectory motion plotting and control mode selection for a space tug with an electric propulsion thruster (EPT) while a SO deorbiting. It presents as well the methodological principles for computing the spacecraft overfly with the low-thrust engines application, including the techniques for the EPT trajectory and thrust vector control modes optimizing while deorbiting.
Contactless methods for deorbiting space objects using an ion beam are examined in detail as a promising approach to developing safe and reliable space debris removal systems.
Application of this method for the space debris deorbiting is being limited by the extra requirement to an ion beam source with a reserve of working medium. Besides, the operational range is limited by several tens of meters due to the plasma beam divergence.
The purpose of this work consists in the efficiency improving of the contactless transportation method for space debris by accounting for the specifics of its motion under the effect of an ion beam, forming control laws for the active spacecraft thrust vector, and plotting its trajectory.
The article theoretically justifies the modes of the space objects deorbiting, and presents analytical solutions for deorbiting time and working medium consumption. The authors obtained scientific results on determining basic characteristics of the SO transportation while deorbiting from low near-Earth orbits.
This approach will allow evaluating effectiveness and identify areas of rational application of various methods for cleaning near-Earth space from space debris.

Keywords:

space debris, contact and non-contact methods, ion beam effects, deorbiting, trajectory optimization, transportation time, working medium consumption, control modes

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