Abstract

The oscillating heat pipe (OHP) is a novel heat-transfer technique used in thermal engineering. Although the OHP offers many technical advantages, it has not yet been actually used in the sky. Motivated by the need to develop a cooling system for use in the balloon-borne General Anti-Particle Spectrometer (GAPS) project, we are developing OHP technologies. To demonstrate the thermal performances of an OHP in real balloon flight conditions, a scaled-down OHP model was launched by a stratospheric balloon in Japan. In this study, we report the results of the flight demonstration.

Highlights

  • The development of the oscillating heat pipe (OHP), or pulsating heat pipe, as a cooling system has grown from the General Anti-Particle Spectrometer (GAPS) project

  • GAPS will conduct this cosmic-ray observation from longduration balloon (LDB) °ights over Antarctica

  • The OHP has many advantages over a conventional heat pipe, including simple fabrication as the capillary tube needs no internal wick, less sensitivity to orientation or gravitational pull, the capacity for large-scale heat transfer, and the ability to adapt to a low heat °ux

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Summary

Introduction

The development of the oscillating heat pipe (OHP), or pulsating heat pipe, as a cooling system has grown from the General Anti-Particle Spectrometer (GAPS) project. The GAPS project requires heat energy of approximately 100 W to be transferred across a distance of more than 2 m This is to be achieved using an OHP with 36 turns. Before moving to full-scale deployment (Okazaki et al, 2014), a °ight This is an Open Access article published by World Scientic Publishing Company. Demonstration has been conducted by mounting a scaled-down OHP as a part of the payload of an engineering balloon experiment called \pGAPS" (prototype-GAPS) (Fuke et al, 2014; Mognet et al, 2014). Initial reports of this OHP °ight demonstration were presented by Fuke et al (2012) and Okazaki et al (2012). We present details of the balloon-°ight demonstration of the \pGAPS OHP" that have not been reported previously

System design
Thermal properties
Mounting as payload
Thermal calculation model
Flight Operation
Heat conductance
Setting variables in thermal model
Thermal calculation results
Summary
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