Investigation on liquid helium pressurization process using a heater in a liquid propellant rocket

In, Sehwan; Jeong, Sangkwon; Kim, Hongseong

doi:10.1016/j.cryogenics.2004.02.010

Cited by 9 publications

(3 citation statements)

References 1 publication

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“…The pressurant is stored in special insulated capsules. Papers on treatment of pressurization systems have not received considerable attention [5][6][7][8][9][10][11][12][13][14][15][16][17][18][19][20][21][22]. In these references, simple relations for initial design of the pressurization systems are used.…”

Section: Introductionmentioning

confidence: 99%

Modeling and simulation of a class of liquid propellant engine pressurization systems

2010

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Section: Introductionmentioning

confidence: 99%

Modeling and simulation of a class of liquid propellant engine pressurization systems

2010

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“…When the propellants are pumped through feedlines, geysering has been an important problem to be considered in designing and operating a rocket propulsion system using cryogenic propellants [5]. There are several approaches to eliminate or suppress geysering, which include utilization of external single-feeding recirculation pipelines [6], subcooled topping [5], liquid helium pressurization [7,8], and injection of helium gas bubbles into the bottom of the oxidizer tank [9]. However, still the most popular technique is the pressurization of the oxidizer tank by injection of noncondensable gas.…”

Section: Introductionmentioning

confidence: 99%

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Kim

et al. 2012

J. Engin. Thermophys.

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The transient thermal behavior in the cryogenic oxidizer tank for the liquid propulsion system of the KSLV-I satellite launching space vehicle is theoretically investigated for the pressurization process by gaseous helium injection followed by the readiness check stage. The numerical model is established using the transient mass and energy conservation of oxygen/helium mixtures both in ullage and liquid regions. At the liquid-gas interface, various modes of heat and mass transfer are considered, including the liquid evaporation and the helium absorption. The present study focuses on the effects of the increasing pressurization level on some of important properties that should be considered in the propulsion system design, such as tank pressure, ullage gas temperature, and evaporation of liquid oxygen. Particularly, the tank pressure drop after the pressurization is investigated in the proposed design of propulsion system. Also, the effect of the initial loading of liquid oxygen in the oxidizer tank is studied and discussed. As for the helium absorption into the liquid region, its mass is negligibly small and it should not be the concern in design and operation of the oxidizer tank system.

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“…However, the previous liquid helium pressurization system needed another ambient and high pressure helium gas to keep the expulsion pressure of the liquid helium tank (3) . The new method using an electric heater was suggested to maintain the expulsion pressure (4) . This novel method makes the whole pressurization system very simple and reliable, because the electric heater power is easy to control.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Liquid Helium Pressurization Method for Liquid Propellant Rocket

Jeong

Kim

et al. 2005

JSME international journal. Ser. B, Fluids and thermal engineer

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The liquid helium pressurization method using an electric heater makes the pressurization system of a liquid propellant rocket very simple and reliable with reducing the volume and the weight of the pressurant tank. In this pressurization system, the selection of the electric heater arrangement and the heating power is critical to its performance. This paper describes how to arrange the heaters and the effect of the heating power in the liquid helium pressurant tank of the liquid propellant rocket. The experiment was performed to find the proper heater arrangement and the results are discussed. The effect of the heating power on the pressurization performance is also investigated through the experiment.

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Investigation on liquid helium pressurization process using a heater in a liquid propellant rocket

Cited by 9 publications

References 1 publication

Modeling and simulation of a class of liquid propellant engine pressurization systems

Modeling and simulation of a class of liquid propellant engine pressurization systems

Transient thermal analysis of a cryogenic oxidizer tank in the liquid rocket propulsion system during the prelaunch helium gas pressurization

Experimental Investigation of Liquid Helium Pressurization Method for Liquid Propellant Rocket

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