Research on advanced rocket engines

JAXA Supercomputer System Annual Report February 2022-January 2023

Report Number: R22EDG20102

Subject Category: Research and Development

Responsible Representative: Toshiya Kimura, Specially appointed advisor, Research and Development Directorate, Research Unit IV
Contact Information: Toshiya Kimura, Research and Development Directorate, Research Unit IV(kimura.toshiya@jaxa.jp)
Members: Kosei Goto, Taku Inoue, Toshiya Kimura, Shinichi Moriya, Mitsuru Shimagaki, Masaharu Takahashi

Abstract

The objective of our work is to accelerate ongoing projects such as RV-X and CALLISTO, which are R&D of small reusable rockets, and future researches on reusable and advanced rocket engines through numerical simulations.

Reference URL

N/A

Reasons and benefits of using JAXA Supercomputer System

It is very useful for researchers who make R&D of advanced rocket engines that various softwares such as CFD and FEM are available.

Achievements of the Year

1. CFD simulations for hydrodynamical characteristics of the electric pump used in an electric pump-fed liquid rocket engine. The effect of heat generation in the motor was also investigated by applying thermal conduction and fluid dynamic coupled simulation to the electric motor and pump.

2. When a small reusable test vehicle is landing, effects of the engine plume on the ground were investigated using CFD simulations (Fig.1).

3. Abaqus was used to estimate the temperature rise of hypersonic vehicles (Fig.2). First, we calculated the heat flux corresponding to the flight trajectory using Computational Fluid Dynamics and applied it to Abaqus as boundary conditions. As a result of examining the temperature history, it was found that the temperature does not rise to the extent that it melts.

4. To realize an electric pump cycle engine, it is necessary to reduce the weight of the combustion chamber. Therefore, a thermal stress analysis was conducted using a heat-resistant alloy for the combustion chamber, and the technical issues were extracted.

Fig.1: Temperature distribution of the plume gas from a 4 ton class rocket engine at 2m from the ground.

Fig.2: Material composition of the hypersonic flight vehicle

Publications

N/A

Usage of JSS

Computational Information

Process Parallelization Methods: N/A
Thread Parallelization Methods: N/A
Number of Processes: 1
Elapsed Time per Case: 1 Second(s)

JSS3 Resources Used

Fraction of Usage in Total Resources*1(%): 0.19

Details

Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.

Computational Resources
System Name	CPU Resources Used (Core x Hours)	Fraction of Usage*2(%)
TOKI-SORA	0.00	0.00
TOKI-ST	26.65	0.00
TOKI-GP	0.00	0.00
TOKI-XM	0.00	0.00
TOKI-LM	0.00	0.00
TOKI-TST	0.00	0.00
TOKI-TGP	0.00	0.00
TOKI-TLM	0.00	0.00

File System Resources
File System Name	Storage Assigned (GiB)	Fraction of Usage*2(%)
/home	113.05	0.10
/data and /data2	306.91	0.00
/ssd	192.62	0.03

Archiver Resources
Archiver Name	Storage Used (TiB)	Fraction of Usage*2(%)
J-SPACE	0.09	0.00

*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.

ISV Software Licenses Used

ISV Software Licenses Resources
	ISV Software Licenses Used (Hours)	Fraction of Usage*2(%)
ISV Software Licenses (Total)	9342.21	6.50

*2: Fraction of Usage：Percentage of usage relative to each resource used in one year.