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The exploration of near-Earth space leads to the appearance of space debris, consisting of spent satellites, spacecraft elements, launch vehicles and upper stages that have exhausted their resources. Deorbiting techniques using inflatable system are an important field of space studies for the mitigation of orbital debris. The choice of rational parameters of the inflatable shell of the braking device provides for the solution of a number of rather complex interdisciplinary tasks. This paper consists analysis possibility of applying inflatable deorbiting system including temperature state and probability of shell destruction.

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Inflatable Deorbiting Systems for Space Debris: Design Parameters and Thermal State

  • 会议论文

  • 发表日期：

    2026年

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  • Elizaveta N. Abramova

摘要

The exploration of near-Earth space leads to the appearance of space debris, consisting of spent satellites, spacecraft elements, launch vehicles and upper stages that have exhausted their resources. Deorbiting techniques using inflatable system are an important field of space studies for the mitigation of orbital debris. The choice of rational parameters of the inflatable shell of the braking device provides for the solution of a number of rather complex interdisciplinary tasks. This paper consists analysis possibility of applying inflatable deorbiting system including temperature state and probability of shell destruction.