JAXA Special Publication JAXA-SP-19-003E

Liquid-Propellant Rocket System Simulation
Report Number: R18EG3215
Subject Category: Research and Development
URL: https://www.jss.jaxa.jp/en/ar/e2018/9146/
Responsible Representative
Eiji Sima, Research and Development Directorate, Research Unit III
Contact Information
Hiedyo Negishi (negishi.hideyo@jaxa.jp)
Members
Yasuhito Kano, Ryutaro Furuya, Tetsuji Ogawa, Takayuki Ito, Hideyo Negishi, Yoichi Ohnishi, Miki Nishimoto,
Yu Daimon, Ashvin Hosangadi, Masaaki Ino, Osamu Fukasawa, Shinji Ohno, Andrea Zambon, TakenoriNakajima, Takashi Amemiya, Yutaka Umemura, Hironori Fujiwara, Hiroumi Tani, Keiichiro Fujimoto, Tetsufumi
Ohmaru, Akiko Kotani, Taroh Fukuda, Mayu Matsumoto, Masashi Toyama, Akimitsu Terunuma
Abstract
Future generation of space transport systems need not only to reduce costs with high propulsion performancebut also to meet the requirements of various missions, for example moon landing, reusable upper stage rocket,
Mars mission, and so on. Liquid-Propellant Rocket System Analysis has an important role to develop the nextgeneration space transport system. Utilizing 3D numerical simulation results of the liquid rocket compornents, thecomponet model is developed for the system analysis. The system analysis will be used for evaluation of thedevelopment and operation for liquid rocket.
Ref. URL: http://www.kenkai.jaxa.jp/eng/research/software/software.html
Reasons for using JSS2
The liquid rocket component model of the system analysis tool is conventionally very simple. With thedevelopment of computer science, even if component models are more complex than before, they can be used fordesign. In addition, high-fidelity CFD clarified physical phenomena in the component, and it became possible todevelop more accurate component models. High-fidelity CFD analysis is essential to clarify the phenomena in theliquid propulsion system, and a wide range of parameter studies that can be used for system analysis are conducted.
JSS2 is used for these high-fidelity CFD analysis.
Achievements of the Year
In order to study the flight control plan of the reusable rocket RV-X, the dynamic characteristics of sloshing(moving the center of gravity of the propellant and tank) in consideration of the shape of the accessories in thepropellant tank were evaluated using CFD (Fig. 1). We developed a sloshing attenuation model from the CFD－254－

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JAXA Supercomputer System Annual Report (April 2018-March 2019)

results (Fig. 2) and provide it to the project. It have contributed to the development of a flight control program.

Fig. 1: Reusable rocket RV-X, CFD results of tank sloshing

Fig. 2: Time evolution of tank center of gravity－255－This document is provided by JAXA.

JAXA Special Publication JAXA-SP-19-003E

Publications
N/A
Usage of JSS2Computational Information
Process Parallelization Methods

MPI

Thread Parallelization Methods

Automatic Parallelization

Number of Processes

1-4

Elapsed Time per Case

150 Hour (s)Resources Used
Fraction of Usage in Total Resources*1 (%): 1.22
Details
Computational Resources
System Name

Amount of Core Time(core x hours)

Fraction of Usage*2 (%)

SORA-MA

1,384,761.92

0.17

SORA-PP

1,780,416.76

14.23

SORA-LM

335.080.16

SORA-TPP

378.390.03

File System Resources
File System Name

Storage Assigned (GiB)

Fraction of Usage*2 (%)/home638.13

0.66/data

23,161.66

0.41/ltmp

13,691.71

1.17

Archiver Resources
Archiver Name

Storage Used (TiB)

J-SPACE

Fraction of Usage*2 (%)
0.31

0.01

*1

: Fraction of Usage in Total Resources: Weighted average of three resource types (Computing, File System,and Archiver).
*2: Fraction of Usage: Percentage of usage relative to each resource used in one year.

－256－

This document is provided by JAXA.