Abstract
The paper describes the most promising ways of de-orbiting small spacecraft: aerodynamic systems, electrodynamic tether systems and systems based on propulsive effectors - liquid, solid-fuel and electroreactive. We selected the design parameters of various options for constructing a small spacecraft de-orbiting system, taking into account the restrictions, and assessed the effectiveness of these options. As a result, we developed a method for selecting design parameters for a small spacecraft de-orbiting system. The method is focused on an assessment of the effectiveness of various options for constructing a de-orbiting system based on several indicators, taking into account the imposed restrictions. In the study, we give examples of implementing the developed method for selecting design parameters for small spacecraft “Aist” and “Aist-2D”. We also consider the composition and scheme of operation of the most effective option of constructing a system for de-orbiting the “Aist” satellite, and reveal the principles of operation of the main components of the system. Thanks to the use of the proposed system, the prototype of the small spacecraft “Aist” can be de-orbited in 96 days when a ballistic life without using the proposed system is 26 years. In the case of the small spacecraft “Aist-2D”, de-orbiting can be done in one day when a ballistic life without using the proposed system is 11 years old.
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