Abstract
The most promising ways to remove small spacecraft from orbit are considered. Design parameters of various variants of construction of the system of small spacecraft removal from orbits are chosen taking into account limitations. The efficiency of these variants is evaluated. Examples of implementation of the developed method of selection of design parameters for small spacecraft "AIST" and "AIST-2D" are given. The composition and operation scheme of the variant chosen as a result of efficiency evaluation of the "AIST" de-orbiting system are considered, and the principles of operation of the main system components are described. With the use of the proposed system, the prototype of the "AIST" small spacecraft can be removed from orbit in 96 days while the period of ballistic existence without the proposed system would be about 26 years, in case of the "AIST-2D" small spacecraft - in one day with the period of ballistic existence without the proposed system of 11 years.
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