Experimental Investigation of Liquid Helium Pressurization Method for Liquid Propellant Rocket

In, Sehwan; Jeong, Sangkwon; Kim, Youngkwon; Cho, Kie-Joo; Oh, Seung-Hyub

doi:10.1299/jsmeb.48.300

Cited by 2 publications

(2 citation statements)

References 3 publications

(3 reference statements)

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Park et al (2005) described a method to determine the optimal size of a liquid helium tank and presented a set of results under a given set of requirements. In et al (2005) studied an electric heater that makes the pressurization system of a liquid propellant rocket very simple and reliable by reducing the volume and the weight of the pressurant tank. The research investigated the effect of the heating power on the pressurization performance through the experiment.…”

Section: Introductionmentioning

confidence: 99%

Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

Mitikov

Shynkarenko

2022

J. Aerosp. Technol. Manag.

View full text Add to dashboard Cite

The work focuses on optimizing the pressurization system's operating performance for a fuel tank of a turbo-pumped liquid propellant rocket engine. This system is the most complex and expensive in a medium-size launch vehicle, after the engine. A new patented methodology of reducing the final mass of a rocket stage is proposed, studied, and validated. The application of the proposed method is efficient at the end of the engine operation sequence during the throttling regime. The calculation method of the helium excess in the high-pressure cylinders uses the model of the real gas. It also involves empirical relations describing nonstationary heat and mass transfer in the system. As an innovative technical solution, the authors propose to estimate excess gas discharge from tanks and cylinders after the engine's last throttling. The practical application of the research allows saving tenths of kilograms of a payload with the implementation of simple modification in the launcher control program. The research results demonstrated the effectiveness of the methodology on the example of the RD-171 fuel tank pressurization system.

show abstract

Section: Introductionmentioning

confidence: 99%

Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

Mitikov

Shynkarenko

2022

J. Aerosp. Technol. Manag.

View full text Add to dashboard Cite

show abstract

“…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.

View full text Add to dashboard Cite

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.

show abstract

Experimental Investigation of Liquid Helium Pressurization Method for Liquid Propellant Rocket

Cited by 2 publications

References 3 publications

Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

Reduction of the Pressurization System Final Mass for a Modern Rocket Launcher

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

Contact Info

Product

Resources

About