Modeling the RL10 with Densified Liquid Hydrogen and Oxygen Propellants

Haberbusch, Mark S.; Skaff, Antony; Nguyen, Cong Tam; Walls, Laurie

doi:10.2514/6.2002-3597

Cited by 4 publications

(1 citation statement)

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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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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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Mathematical model and experimental results for cryogenic densification and sub-cooling using a submerged cooling source

et al. 2012

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Among the many factors that determine overall rocket performance, propellant density is important because it affects the size of the rocket. Thus, in order to decrease the size of a rocket, it may be desirable to increase the density of propellants. This study analyzes the concept of increasing the propellant density by employing a cooling source submerged in the liquid propellant. A simple, mathematical model was developed to predict the rate of densification and the propellant temperature profile. The mathematical model is generic and applicable to multiple propellants. The densification rate was determined experimentally by submerging a cooling source in liquid oxygen at constant, positive pressure, and measuring the time rate of change in temperature with respect to vertical position. The results from the mathematical model provided a reasonable fit when compared to experimental results.

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