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In order to avoid pollution of the near-Earth space out-of-service small spacecrafts could be transferred to the disposal orbits in dense atmosphere with the help of inflatable decelerator. The issues of aerodynamics and heat transfer are of key importance for such systems design. The movement conditions in a low Earth orbit of a spherical inflatable aerodynamic decelerator designed for small spacecrafts removal are considered. The preliminary results of thermal analysis of the decelerator made of polymer film with the surface metallization are presented.

On the way to the optimal design of an inflatable aerodynamic decelerator of space debris removal system for CubeSat nanosatellites