液态氢
航空航天工程
海洋工程
航空学
环境科学
燃油箱
氢
汽车工程
工程类
物理
量子力学
作者
Nikola Gavrilović,Sofia Mertika,Jean‐Marc Moschetta,Joshua Schimpf,Go-Ryong Park,Seoyoung C. Kim
出处
期刊:Journal of Aircraft
[American Institute of Aeronautics and Astronautics]
日期:2024-09-19
卷期号:: 1-12
摘要
A lightweight, 12 L liquid hydrogen fuel tank has been designed, fabricated, and tested with the aim of optimizing boil-off rates while minimizing the weight of a complete propulsion system intended to be integrated into an unmanned aerial vehicle. After looking at several different insulation schemes, the system was optimized as two concentric, lightweight titanium cylinders with high vacuum and multilayer insulation in between. The thickness of the multilayer insulation and the design of support structures were optimized to reduce the overall weight of the tank. This paper focuses on characterizing the boil-off rate of a small liquid hydrogen tank in relation to ambient temperature and fuel level. Additionally, it addresses the analysis of the instrumented transfer line between the reservoir and the operating fuel cell, presenting pressure and temperature measurements for each component of the transfer line. The efficiency of the heat exchanger under natural and forced convection is also discussed. The key contribution of the experimental campaign lies in demonstrating an average boil-off rate of [Formula: see text] over 45 h. This significantly surpasses the limits of ultra-long-range flight achievable with alternative electric energy sources. Furthermore, the paper highlights the importance of the variable boil-off with time and its impact on aircraft performance.
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