Advancement in cryogenic propulsion system performance through propellant densification

Lak, Tibor; Lozano, Martin; Tomsik, Thomas M.

doi:10.2514/6.1996-3123

Cited by 13 publications

(9 citation statements)

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“…A K‐T decision‐making method has been conducted to determine the optimization scheme for producing, loading and maintaining the subcooling degree. Lak et al . reported that in order to design and build an LH 2 densification unit prototype and to validate thermodynamic characteristics of the tanks, a technology demonstration program was proposed by Rockwell and NASA.…”

Section: Introductionmentioning

confidence: 99%

“…A K-T decision-making method has been conducted to determine the optimization scheme for producing, loading and maintaining the subcooling degree. Lak et al [10] reported that in order to design and build an LH 2 densification unit prototype and to validate thermodynamic characteristics of the tanks, a technology demonstration program was proposed by Rockwell and NASA. Previous studies [11][12][13] described the ground loading systems of Saturn I/IB/V launch vehicle in detail, including system facilities of LH 2 and LO 2 , test system operation and prelaunch sequences.…”

Section: Introductionmentioning

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: Introductionmentioning

confidence: 99%

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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“…GRC continued development for another 8 years with several advances working with the X-33 program, including construction of two densifier units (0.9 kg/sec and 3.6 kg/sec), and conducted several transfer and loading demonstrations [7][8][9]. At this time, the Space Shuttle program considered switching to densified propellants as an upgrade to launch more mass to orbit, but operational concerns and the need for a costly engine recertification effort resulted in the decision to pursue the super-lightweight external tank modification instead [10]. NASA continued development of densifier systems with the 2nd Generation Reusable Launch Vehicle program, funding three separate contracts to build prototype units and investigate refrigeration technologies [11].…”

Section: Introductionmentioning

confidence: 99%

Large scale production of densified hydrogen to the triple point and below

Swanger

Notardonato

Fesmire

et al. 2017

IOP Conf. Ser.: Mater. Sci. Eng.

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Abstract. Recent demonstration of advanced liquid hydrogen storage techniques using Integrated Refrigeration and Storage technology at NASA Kennedy Space Center led to the production of large quantities of densified liquid and slush hydrogen in a 125,000 L tank. Production of densified hydrogen was performed at three different liquid levels and LH2 temperatures were measured by twenty silicon diode temperature sensors. Overall densification performance of the system is explored, and solid mass fractions are calculated. Experimental data reveal hydrogen temperatures dropped well below the triple point during testing, and were continuing to trend downward prior to system shutdown. Sub-triple point temperatures were seen to evolve in a time dependent manner along the length of the horizontal, cylindrical vessel. The phenomenon, observed at two fill levels, is detailed herein. The implications of using IRAS for energy storage, propellant densification, and future cryofuel systems are discussed. IntroductionFluid-based fuels and/or oxidizers are routinely stored on-board vehicles of various types in order to provide chemical potential for an engine. In the vast majority of these applications the fluids are stored in a liquid state due to the significantly larger stored energy capacity compared to the gaseous phase, and can be kept at much lower pressures, avoiding the need for heavy pressure vessels. In either case, the key point is that the fluid acts as an energy carrier, therefore, the denser the fluid the greater the energy stored in a given volume. This is especially important in applications where the transportation of energy in fluid form is the express purpose, such as in ocean-going and roadable tankers. The term "densification" refers to the process of thermodynamically manipulating a fluid with the intent of increasing its density above that of a typical reference value, thereby increasing its energy storage potential. Reference values usually correspond to atmospheric conditions (temperature, pressure, or both), and in the case of cryogenic propellants such as liquid hydrogen (LH2), liquid methane or liquefied natural gas (LNG), and liquid oxygen (LOX), the reference density is that realized at the normal boiling point (NBP); i.e. when the fluid is completely saturated at atmospheric pressure.Historically, the maximum attainable cryofuel density has corresponded to the NBP storage condition. This constraint has been an important driver for the design of any application that utilizes cryogenic propellants, most notably chemical combustion-powered launch vehicles, by effectively dictating the required tank volumes. Therefore, increasing the density of the propellants can have a substantial effect on the overall vehicle design and/or performance. This is especially true for rockets

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“…Many have conducted studies for propellant densification [1] [2] [3]. Most of the studies suggest to place the densification operation between the ground storage tank and launch vehicle [4] [5] [6].…”

Section: Introductionmentioning

confidence: 99%

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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Advancement in cryogenic propulsion system performance through propellant densification

Cited by 13 publications

References 0 publications

Performance evaluation on ground loading systems of cryogenic propellants

Performance evaluation on ground loading systems of cryogenic propellants

Large scale production of densified hydrogen to the triple point and below

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

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