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Heat Transfer Research
Fator do impacto: 0.404 FI de cinco anos: 0.8 SJR: 0.264 SNIP: 0.504 CiteScore™: 0.88

ISSN Imprimir: 1064-2285
ISSN On-line: 2162-6561

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Heat Transfer Research

DOI: 10.1615/HeatTransRes.2016007682
pages 309-318

EXPERIMENTAL INVESTIGATION OF RADIATING PIN FIN WITH CYLINDRICAL AND CONICAL CAVITIES

J. Ganesh Murali
Department of Automobile Engineering, Karpagam College of Engineering, Coimbatore - 641032, India
Subrahmanya S. Katte
Department of Mechanical Engineering, PES Institute of Technology, Bangalore - 560100, India

RESUMO

The overall thermal control of a satellite is achieved by balancing the energy emitted by the spacecraft as radiation against the energy dissipated by its internal components plus the energy absorbed from the environment. Since mass is at a premium on a spacecraft, the space radiator used in its temperature control system needs to be optimized with respect to mass. An experimental study was conducted to provide information about the heat radiated to the space from a pin fin with cylindrical and conical cavities. The pin fin with cylindrical cavity dissipates 1.3 times more heat and 3.2 times more heat loss per unit mass than a solid pin fin in vacuum. Further the pin fin with conical cavity losses 1.7 times more heat and 2.3 times more heat loss per unit mass compared to a solid pin fin in vacuum. It is a significant achievement in the enhancement of the heat transfer characteristics of the radiating fin.

Palavras-chave: radiating fin, cavity effect

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