Optimal way for choosing parameters of spacecraft’s screen-vacuum heat insulation
- Authors: Formalev V.F.1, Kolesnik S.A.1, Selin I.A.1, Kuznetsova E.L.1
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Affiliations:
- Moscow Aviation Institute (National Research University)
- Issue: Vol 55, No 1 (2017)
- Pages: 101-106
- Section: Heat and Mass Transfer and Physical Gasdynamics
- URL: https://journals.rcsi.science/0018-151X/article/view/157045
- DOI: https://doi.org/10.1134/S0018151X17010096
- ID: 157045
Cite item
Abstract
The heat transfer in multiple plate sandwiches of spacecraft’s screen-vacuum heat insulation is simulated for determining the characteristics of heat shielding against long-term solar heat flux. To choose optimal characteristics of heat shielding, it is necessary to determine precisely the number of plates and their peculiarities. The new, absolutely stable method for solving numerically heat transfer problems is presented. We obtain results showing that the screen-vacuum insulation is characterized by low heating-up inertance that is unacceptable. To remove this effect, the inertial heat shielding is used on the internal surface of the heat shielding and its state is examined.
About the authors
V. F. Formalev
Moscow Aviation Institute (National Research University)
Author for correspondence.
Email: formalev38@mail.ru
Russian Federation, Moscow
S. A. Kolesnik
Moscow Aviation Institute (National Research University)
Email: formalev38@mail.ru
Russian Federation, Moscow
I. A. Selin
Moscow Aviation Institute (National Research University)
Email: formalev38@mail.ru
Russian Federation, Moscow
E. L. Kuznetsova
Moscow Aviation Institute (National Research University)
Email: formalev38@mail.ru
Russian Federation, Moscow
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