Liquid hydrogen has distinct advantages as an aircraft fuel. These include a specific heat of combustion 2.8 times greater than gasoline or jet fuel and zero carbon emissions. It can be utilized by fuel cells, turbine engines and internal combustion engines. The high heat of combustion is particularly important in the design of long endurance aircraft with liquid hydrogen enabling cruise endurance of several days. However, the mass advantage of the liquid hydrogen fuel will result in a mass advantage for the fuel system only if the liquid hydrogen tank and insulation mass is a small fraction of the hydrogen mass. The challenge is producing a tank that meets the mass requirement while insulating the cryogenic liquid hydrogen well enough to prevent excessive heat leak and boil off. In this paper, we report on the design, fabrication and testing of a liquid hydrogen fuel tank for a prototype high altitude long endurance (HALE) demonstration aircraft. Design options on tank geometry, tank wall material and insulation systems are discussed. The final design is an aluminum sphere insulated with spray on foam insulation (SOFI). Several steps and organizations were involved in the tank fabrication and test. The tank was cold shocked, helium leak checked and proof pressure tested. The overall thermal performance was verified with a boil off test using liquid hydrogen.
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12 June 2012
ADVANCES IN CRYOGENIC ENGINEERING: Transactions of the Cryogenic Engineering Conference - CEC, Volume 57
13–17 June 2011
Spokane, Washington, USA
Research Article|
June 12 2012
Design, fabrication and testing of a liquid hydrogen fuel tank for a long duration aircraft
Gary L. Mills;
Gary L. Mills
Ball Aerospace and Technologies Corporation Boulder, Colorado, 80301,
USA
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Brian Buchholtz;
Brian Buchholtz
Ball Aerospace and Technologies Corporation Boulder, Colorado, 80301,
USA
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Al Olsen
Al Olsen
The Boeing Company Huntington Beach, CA,
USA
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AIP Conf. Proc. 1434, 773–780 (2012)
Citation
Gary L. Mills, Brian Buchholtz, Al Olsen; Design, fabrication and testing of a liquid hydrogen fuel tank for a long duration aircraft. AIP Conf. Proc. 12 June 2012; 1434 (1): 773–780. https://doi.org/10.1063/1.4706990
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