JAXA Supercomputer System Annual Report April 2017-March 2018

Report Number: R17EU0904

Subject Category: Space and Astronautical Science

PDF available here

• Responsible Representative: Eiichi Sato, Department of Space Flight Systems, Institute of Space and Astronautical Science
• Contact Information: Ikkoh Funaki funaki.ikkoh@jaxa.jp
• Members: Shitan Tauchi, Hiroyuki Arai

Abstract

Numerical and physical modeling of Magnetoplasmadynamic arcjet and other advanced spacecraft propulsion for future large space mission are conducted. Also, based on the modeling, performance prediction tool is organized.

Reference URL

N/A

Reasons for using JSS2

Enough calculation resources (CPU and memory) are required to perform plasma simulation and to optimize spacecraft propulsion's performance.

Achievements of the Year

To clarify the plasma behavior on a self-field magnetoplasmadynamic thruster (SF-MPDT) at the critical current operation using hydrogen as a propellant, the flow-field was simulated numerically. In the simulation code, the ion-slip effect is incorporated as a numerical model. The numerical simulation was conducted for discharge current J = 5 kA, 10 kA (critical current) and mass flow rate of 0.4 g/s, in order to understand the plasma conditions at critical current level. At the critical current, the current path was extended to downstream of discharge chamber by increasing magnetic flux density and Hall effect, therefore the pressure raised at cathode tip and central axis. The blowing force was increasing at the critical current, because the current distribution at cathode tip was 5 times as large as the case of 5 kA and the self-induced magnetic field was equally increased. The ion-slip parameter was significantly occurred in large part of discharge chamber at the critical current (Sion greater than unity). The ion-slip heating was occurred at the supersonic region, and its caused to suppress the gas dynamic thrust.

Publications

■ Presentations

1)Shin Tauchi, Akira Kawasaki, Masakatsu Nakane, Kenichi Kubota, Ikkoh Funaki, Numerical Analysis of the Effect of Cathode Configuration on Hydrogen MPD Thruster Performance, Asian Joint Conference on Propulsion and Power, AJCPP2018-027, March 2018, Xiamen.

Usage of JSS2

Computational Information

• Process Parallelization Methods: MPI
• Thread Parallelization Methods: Automatic Parallelizatio
• Number of Processes: 32 - 512
• Elapsed Time per Case: 10.00 hours

Resources Used

Fraction of Usage in Total Resources*1(%): 0.04

Details

Please refer to System Configuration of JSS2 for the system configuration and major specifications of JSS2.

*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.

JAXA Supercomputer System Annual Report April 2017-March 2018