Mathematical Modeling, Parametric Study and Design of Loop Heat Pipe for Space Application

Abstract

Loop pipe is termed as passive two phase heat transfer device. In space applications the biggest challenge is to have the spacecraft payloads within the acceptable temperature limits. As of now ways available are active and passive way of controlling the temperature. Active way will have the use of external pumps or devices which need power supply. Passive thermal control means maintaining the temperature within the spacecraft without using external source. Current research in this field involves Phase Change Materials, Heat Pipes, Loop Heat Pipe, Pulsating heat pipe etc. In this study, mathematical modeling and parametric study of loop heat pipe components has been carried out. Steady state operating temperature for loop heat pipe working with water and Ammonia as fluid has been determined. In this thesis theoretical investigation has been carried out to find temperature, convective heat transfer co-efficient, pressure drop at each section. Steady state has been achieved by two methods. One is IC (Iterative Converegence Scheme) and second is SSC scheme (Steady State Convergence). Parametric study is done to see the effect of each parameters on Steady State Operating Temperature (SSOT) and to understand its significance in working of LHP. Effect of different heat loads through the loop has been studied to find Steady State Operating Temperature (SSOT). Mathematical model has been carried out in Dev C++ software and is compared with experimental results available in literature for SSOT as well as heat ratios at different heat loads for the validation purpose. In-depth algorithm and flowchart have been generated for the solution method and also to touch upon the issues which are not being explained in open literature in depth.