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Abstract <p>The paper presents relations for calculation of the thermal loads and trajectory of motion and its optimization during the spacecraft reentry with the second space velocity into the Earth atmosphere. The aerodynamic characteristics of the spacecraft have been determined. Relations for designing and optimization of the weight of a two-layer indestructible thermal shield are given. The trajectory of motion during the aerodynamic maneuver has been generated. The convective and radiative heat fluxes have been calculated. Heat transfer analysis for the model descent trajectory has been carried out. Optimal thicknesses of thermal shields made of different materials have been obtained. The results confirm the principal possibility of creating indestructible thermal shield for the considered class of spacecraft.</p>

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Optimization of Spacecraft Thermal Shield for Crew Return after Lunar Mission

  • 期刊论文

  • 发表日期：

    2025年6月1日

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  • A. V. Nenarokomov,
  • D. L. Reviznikov,
  • I. A. Nikolichev,
  • M. O. Salosina,
  • A. S. Grinenko

摘要

Abstract

The paper presents relations for calculation of the thermal loads and trajectory of motion and its optimization during the spacecraft reentry with the second space velocity into the Earth atmosphere. The aerodynamic characteristics of the spacecraft have been determined. Relations for designing and optimization of the weight of a two-layer indestructible thermal shield are given. The trajectory of motion during the aerodynamic maneuver has been generated. The convective and radiative heat fluxes have been calculated. Heat transfer analysis for the model descent trajectory has been carried out. Optimal thicknesses of thermal shields made of different materials have been obtained. The results confirm the principal possibility of creating indestructible thermal shield for the considered class of spacecraft.