Calculation of Heat Loads in Analysis of Superorbital Entry of Spacecraft into Atmosphere of the Earth

IF 1.3 4区工程技术 Q3 ENGINEERING, MECHANICAL

Journal of Engineering Thermophysics Pub Date : 2023-11-08 DOI:10.1134/S1810232823030050

D. L. Reviznikov, A. V. Nenarokomov, M. S. Konstantinov, I. A. Nikolichev, A. V. Morzhukhina, L. M. Chernova

引用次数: 0

Abstract

Correlations for calculation of heat loads during a return of spacecraft at the second cosmic velocity are given. Analysis of the heat transfer for a model descent trajectory has been carried out. The convective and radiative heat fluxes, the relative heat transfer coefficient, and the radiative-equilibrium surface temperature have been calculated. The results obtained are a basis for design and optimization of the heat shield of spacecraft.

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航天器超轨道进入地球大气层分析中的热负荷计算

给出了航天器以第二宇宙速度返回时热负荷的计算关系式。对模型下降轨迹的传热进行了分析。计算了对流和辐射热通量、相对传热系数和辐射平衡表面温度。所得结果为航天器隔热罩的设计和优化提供了依据。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

Journal of Engineering Thermophysics THERMODYNAMICS-ENGINEERING, MECHANICAL

CiteScore

2.30

自引率

12.50%

发文量

审稿时长

3 months

期刊介绍： Journal of Engineering Thermophysics is an international peer reviewed journal that publishes original articles. The journal welcomes original articles on thermophysics from all countries in the English language. The journal focuses on experimental work, theory, analysis, and computational studies for better understanding of engineering and environmental aspects of thermophysics. The editorial board encourages the authors to submit papers with emphasis on new scientific aspects in experimental and visualization techniques, mathematical models of thermophysical process, energy, and environmental applications. Journal of Engineering Thermophysics covers all subject matter related to thermophysics, including heat and mass transfer, multiphase flow, conduction, radiation, combustion, thermo-gas dynamics, rarefied gas flow, environmental protection in power engineering, and many others.