Performance tests of a liquid hydrogen propellant densification ground support system for the X33/RLV

Tomsik, Thomas M.

doi:10.2514/6.1997-2976

Cited by 17 publications

(11 citation statements)

References 1 publication

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“…. Four‐stage hydrogen compressors reduced pressure of heat exchanger bath to 8.274 kPa to make the temperature of LH 2 decrease to 14.11 K. The LH 2 flowing through the filling pipelines passed through the tube side of the heat exchanger and was subcooled to approximately 15 K …”

Section: Analysis Of Application Cases For Many Countriesmentioning

confidence: 99%

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Performance evaluation on ground loading systems of cryogenic propellants

Xie

Wang

2017

Asia-Pacific J Chem Eng

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To study and compare the merits and demerits of different ground loading systems for cryogenic propellants, three kinds of schemes have been classified according to their loading status: boiling point loading scheme, subcooled direct loading scheme and subcooled cycled loading scheme. Aiming at the three kinds of schemes mentioned previously, related mathematical models of ground storage tanks, filling pipelines and launch vehicle tanks are established by means of a thermal resistance analysis method, lumped parameter method and one‐dimensional finite difference method. Based on the thermodynamic analysis, a K‐T decision‐making method is adopted to determine the preferred scheme. Meanwhile, application situations of multiple ground loading systems in different countries have been analyzed in detail. The researches show that the boiling point loading scheme is the best choice in the aspect of comprehensive performance. However, the subcooled cycled loading scheme is preferable to the case of payload as design objective for the long‐term development. The classified schemes proposed in this paper reveal the feasibility and practicality in actual application of ground loading systems of cryogenic propellants. The study also provides theoretical basis and technological support to design or improve the ground loading systems of cryogenic propellants in the future. © 2017 Curtin University and John Wiley & Sons, Ltd.

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Section: Analysis Of Application Cases For Many Countriesmentioning

confidence: 99%

“…However, there are still some deficiencies for cryogenic propellants, such as low boiling point, low density and low surface tension. These shortcomings may bring many challenges in engineering applications simultaneously …”

Section: Introductionmentioning

confidence: 99%

Performance evaluation on ground loading systems of cryogenic propellants

Xie

Wang

2017

Asia-Pacific J Chem Eng

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“…Densified cryogenic liquid propellants have the benefit of increasing vehicle payload performance or decreasing vehicle mass, decreasing systemoperating pressures, increasing engine system life, and increasing engine and vehicle safety margins [4][5][6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Hydrogen/Oxygen Propellant Densifier Using a Two-Stage Pulse Tube Cryocooler

Nguyen¹,

Yeckley²,

Culler³

et al. 2004

AIP Conference Proceedings

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A unique, patent pending, thermoacoustic propellant densifier, that simultaneously densifies liquid hydrogen and liquid oxygen propellants for aerospace vehicles is introduced. The thermoacoustic densifier consists of a two-stage pulse tube cryocooler that operates at 30 Hz using helium as the working fluid. The extremely reliable pulse tube has no moving parts, is water cooled, and is acoustically driven. The pulse tube has been driven by a Thermoacoustic Stirling Heat Engine (TASHE) and a linear flexure bearing compressor. A laboratory prototype was designed, fabricated, and tested at the Sierra Lobo, Inc. facility in Milan, Ohio. Unique design features include a removable 2 nd stage for easy testing of low temperature regenerator materials and an advanced aftercooler design geometry. A system description will be presented and experimental data of the pulse tube performance will be compared with REGEN 3.2 and other analytical predictions.

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“…Studies have shown 1 that the lift-off mass of cryogen liquid fueled launch vehicles can be reduced from 15 to 32 percent by subcooling the cryogen as compared to fueling with normal boiling point (NBP) fluids. The Taurus II medium lift launch vehicle engine uses RP-1 fuel and liquid oxygen.…”

Section: Introductionmentioning

confidence: 99%

TAURUS II launch vehicle lox subcooler

McIntosh¹

2012

AIP Conference Proceedings

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The Orbital Sciences Taurus II medium lift launch vehicle utilizes first stage engines fueled by liquid oxygen and RP-1. Performance of the Taurus II is enhanced by densifying the liquid oxygen from a saturation temperature of 94 K to a subcooled temperature of 77.9 K. Subcooling the 75.07 kg/s liquid oxygen flow is accomplished in a 1.907 megawatt heat exchanger cooled by a flow of 9.62 kg/s ambient pressure liquid nitrogen. Design, fabrication, insulation and testing of the densification heat exchanger is described in this paper.

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Performance tests of a liquid hydrogen propellant densification ground support system for the X33/RLV

Cited by 17 publications

References 1 publication

Performance evaluation on ground loading systems of cryogenic propellants

Performance evaluation on ground loading systems of cryogenic propellants

Hydrogen/Oxygen Propellant Densifier Using a Two-Stage Pulse Tube Cryocooler

TAURUS II launch vehicle lox subcooler

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