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Numerical modelling and simulation of heat pipe receiver

Xiaohong Gui (School of Aviation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China)
Xiugan Yuan (School of Aviation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China)
Xiange Song (School of Aviation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China)
Wq Xu (School of Aviation Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing, People's Republic of China)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Article publication date: 1 July 2006

942

Abstract

Purpose

In this paper, the purpose of research is to verify good thermal performance of heat pipe receiver.

Design/methodology/approach

Mathematical model was set up, numerical calculation method was offered. Calculation results were compared with experimental results, with those of NASA project, and those of the basis heat receiver.

Findings

Simulation results show that heat pipe receiver involving heat pipe has the performance of perfect heat transfer and ideal identical temperature, the axial temperature difference of heat pipe is small, PCM canisters situated in different places of heat pipe can melt simultaneously and uniformly. At the same time, normal operation of wick ensures the uniformity of heat pipe circumference temperature, thus heat pipe receiver avoids phenomena of thermal spot. In addition, heat pipe receiver has axial and radial performance of ideal identical temperature, all PCM canisters can freeze simultaneously at the end of eclipse periods, and freeze fully at last, so heat pipe receiver avoids thermal ratcheting.

Originality/value

The research in this paper can be used to design heat pipe receiver.

Keywords

Citation

Gui, X., Yuan, X., Song, X. and Xu, W. (2006), "Numerical modelling and simulation of heat pipe receiver", Aircraft Engineering and Aerospace Technology, Vol. 78 No. 4, pp. 315-320. https://doi.org/10.1108/17488840610675591

Publisher

:

Emerald Group Publishing Limited

Copyright © 2006, Emerald Group Publishing Limited

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