The Development of Structural Design and the Selection of Design Parameters of Aerodynamic Systems for De-orbiting Upper-stage Rocket Launcher

Authors

  • A.P. Alpatov Institute of Technical Mechаnics, the NAS of Ukraine and the State Space Agency of Ukraine
  • O.S. Palii Institute of Technical Mechаnics, the NAS of Ukraine and the State Space Agency of Ukraine
  • О.D. Skorik Institute of Technical Mechаnics, the NAS of Ukraine and the State Space Agency of Ukraine

DOI:

https://doi.org/10.15407/scine13.04.029

Keywords:

aerodynamic deorbit system, space debris, space factors, upper-stage rocket launcher

Abstract

The aerodynamic systems for upper-stage rocket launcher de-orbit have been analyzed. The feasibility and possibility of creating aerodynamic inflatable deorbit systems have been established. A mathematical model of upper-stage rocket launcher orbital motion has been developed. The aerodynamic deorbit system parameters for various configurations neglecting effects of space factors have been calculated. The effect of space factors on the aerodynamic deorbit system has been estimated. The effect of atomic oxygen and cosmic vacuum (sublimation) has been showed to lead to a decrease in shell thickness, while space debris causes an increase in consumption of working substance to inflate shell. The structural design has been selected and aerodynamic deorbit system parameters have been calculated with effect of space factors taken into account.

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Published

2024-08-28

How to Cite

Alpatov, A., Palii, O., & Skorik О. (2024). The Development of Structural Design and the Selection of Design Parameters of Aerodynamic Systems for De-orbiting Upper-stage Rocket Launcher. Science and Innovation, 13(4), 29–39. https://doi.org/10.15407/scine13.04.029

Issue

Vol. 13 No. 4 (2017): Science and Innovation

Section

Research and Engineering Innovative Projects of the National Academy of Sciences of Ukraine

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