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

Kim, K. H.; Ko, Hyung–Jong; Kim, K.; Jung, Yong Hun; Oh, Shi-Hwan; Cho, K. J.

doi:10.1134/s1810232812010018

Cited by 19 publications

(4 citation statements)

References 14 publications

(14 reference statements)

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“…Particular issues of the use of helium for pressurization have been considered in the technical (patent) literature. The process of gas pressure drops in a tank with an oxidizer which takes place after its prelaunch pressurization with helium, was studied in the article [8]. The article [17] is devoted to mathematical modeling of phase transitions in the system "cryogenic liquid-free volume of a tank with helium".…”

Section: Literature Reviewmentioning

confidence: 99%

Untitled

2021

Kosm. nauka tehnol.

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To find and confirm the possibility of hydrogen peroxide tank pressurization using high-temperature pressurization gas (~1100 К) with a high percentage of steam (up to 70 %) without its losses.Research methods. Mathematical modeling of pressurization system parameters with the theory of mass transfer and thermodynamic of variable mass bodies have been used.Results. The conducted research allowed us to find and confirm the possibility of using a new pressurization method with additional sources of heat and elaborate recommendations for its appliance during pressurization time.Scientific novelty. The main processes have been determined, which prevent implementation of the efficient high-temperature pressurization system of the tank with the hydrogen peroxide using peroxide decomposition products. The main obstacle is the volume condensation of vapor in the free volume of the tank when heat exchange processes with boundary surfaces take place. For the first time, by means of theoretical calculations, the expediency and rationality of using the additional sources of heat such as high-temperature combustion product of solid-fuel gas generator based on sodium azide have been proved. Using of this additional source for the first 30 seconds of engine operation has been proved.Practical value. Methodology of pressurization system parameters' calculation was supplemented with discovered thermodynamic relation, which allowed us to calculate the amount of vapor and take some measures to eliminate the condensation. Results of the research allowed the designation of the pressurization system for the highly concentrated hydrogen peroxide tank with a high value of length to diameter relation with its high-temperature decomposition products.

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Section: Literature Reviewmentioning

confidence: 99%

Untitled

2021

Kosm. nauka tehnol.

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“…Holt et al (2000) studied an integrated generalized simulation program model for the helium pressurization system's fluid system, where they predicted pressure and temperature values correlate with data collected experimentally. The study of Kim et al (2012) describes transient thermal behavior in the cryogenic oxidizer tank for the liquid propulsion system. In the fuel tank during helium input pressure, growth was investigated with close attention.…”

Section: Introductionmentioning

confidence: 99%

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

Mitikov

Shynkarenko

2022

J. Aerosp. Technol. Manag.

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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.

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“…Kim et al . investigated the thermodynamic behavior of a cryogenic oxidizer tank, which was subject to the tank pressurization using the helium injection. The effects of the increasing pressurization level on such parameters as tank pressure, ullage gas temperature, and evaporation of liquid oxygen were focused.…”

Section: Introductionmentioning

confidence: 99%

Numerical investigation of pressurization performance in cryogenic tank of new‐style launch vehicle

Wang

Zhao

et al. 2013

Asia-Pacific J Chem Eng

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The pressurization performance of cryogenic tanks during discharge is investigated by a computational fluid dynamic approach. A series of cases accounting for the effects of various influence factors such as inlet gas temperature, ramp time of inlet gas temperature, wall thickness, outflow rate, injector structure, and liquid supercooling on pressurization behaviors are computed and analyzed successively. Several valuable conclusions have been drawn as follows: (1) Increasing inlet gas temperature, applying a thin wall to construct the tank, and increasing the outflow rate are beneficial to the reduction of gas requirements, (2) Ramp process and use of a straight pipe injector may lead to an excessive pressure drop at the beginning of discharge, (3) Use of straight pipe injector can remarkably reduce the gas requirement but lead to a large loss of liquid propellant as well as a large weight of final ullage gas, and (4) The mode of mass transfer within the tank is close related to the injector structure and liquid supercooling. A trend of mass transfer toward evaporation can be observed by increasing the liquid temperature, especially for the straight pipe injector case. Generally, the results of this paper might be beneficial to the design and optimization of a pressurization system. © 2013 Curtin University of Technology and John Wiley & Sons, Ltd.

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

Cited by 19 publications

References 14 publications

Untitled

Untitled

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

Numerical investigation of pressurization performance in cryogenic tank of new‐style launch vehicle

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