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Hybrid Radiator for Spacecraft Thermal Control Systems

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Abstract

A radiator with a two-layer hybrid structure is proposed for thermal control systems in spacecraft. Mathematical modeling confirms the efficiency of the emitting surface. On that basis, without loss of reliability, the heat pipes may be eliminated, and consequently the radiator mass is significantly decreased.

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Authors and Affiliations

  1. Moscow Aviation Institute, Moscow, Russia

    A. E. Belyavskii, N. S. Kudryavtseva & A. E. Sorokin

Authors
  1. A. E. Belyavskii
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  2. N. S. Kudryavtseva
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  3. A. E. Sorokin
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Correspondence to A. E. Belyavskii, N. S. Kudryavtseva or A. E. Sorokin.

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Translated by B. Gilbert

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Belyavskii, A.E., Kudryavtseva, N.S. & Sorokin, A.E. Hybrid Radiator for Spacecraft Thermal Control Systems. Russ. Engin. Res. 42, 57–59 (2022). https://doi.org/10.3103/S1068798X22010038

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  • DOI: https://doi.org/10.3103/S1068798X22010038

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