JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0120

• Responsible Representative: Takashi Kubota(Research and Development Directorate, Research Unit I)
• Contact Information: Takahiro Nakamura(nakamura.takahiro@jaxa.jp)
• Members: Seiji Tsutsumi, Hiroyuki Ito, Takahiro Nakamura
• Subject Category: Space(Rocket)

Abstract

The SS-520 No.4 has the performance to launch the 3 kg mass microsatellite 'TRICOM-1' into the low earth orbit. This rocket launched at 15 January 2017 [JST] however satellite could not be into the orbit due to the rocket system anomaly. According to 1st stage flight results, the flight trajectory and impact point are as a planned. It was confirmed that setting of aerodynamic characteristics in orbit planning was appropriate. In addition, condition of aerodynamic heating was also appropriate from rocket telemetry data.

Goal

Objective of this project is the development and demonstration of rocket related equipment developed by private businesses through launching microsatellite by 'SS-520 No.4 rocket'. This activity aims to be realized the advancement and growthiest of space related technologies by extracting the task of development of the space equipment by the private businesses with feedback to the existing rocket technology.

Objective

The microsatellite launch rocket of SS-520 No.4 is improved type rocket of the 2nd stage sounding rocket of SS-520 by adding the 3rd stage motor. In order to promote development of rocket with less system margin of launch performance in short period time, this activity has to promote appropriately and swiftly developing process in following points;

A) Setting the aerodynamic coefficient set for orbit planning.

B) Setting the environmental condition from aerodynamic effect on each parts of rocket system.

References and Links

N/A

Use of the Supercomputer

- Due to the less system margin of SS-520 No.4, the proportion of drag generation at each part of rocket body and reduce low-drag shape are investigated by Computational Fluid Dynamics (CFD) analysis. These results are feedbacked to the rocket design.

- As the environmental condition to each part of rocket body, distributions of aerodynamic heat flux and aerodynamic force are evaluated by CFD analysis. These conditions are used for mechanical design of rocket body.

- Aerodynamic characteristics (especially drag coefficient and normal force coefficient) are evaluated by CFD analysis including microprojections on the rocket surface. These values are applied as a baseline for orbit planning.

- In order to show the flight safety requirement is satisfied even in anomaly flight such as a early separation cases, CFD analysis in anomaly case are conducted and aerodynamic characteristics are set for anomaly flight trajectory analysis.

Necessity of the Supercomputer

Although it must be check the result carefully in evaluation, CFD analysis utilizing supercomputer system has following advantage compared with wind tunnel testing;

A) Quick responsivity to evaluation of various design

B) Wide range evaluation of analysis conditions from model to real scale

C) Be able to evaluate surface distribution and microstructure of flow mechanism

As a result of quick cycle evaluation in development and designing stage utilizing supercomputer system, the rocket was able to be launched in short time development. This implies CFD analysis utilizing supercomputer system are useful tools for reduce the time and risk in rocket development

Achievements of the Year

1. Aerodynamic force and heat flux to each part of rocket body

Distributions of aerodynamic heat flux and aerodynamic force are evaluated in nominal flight trajectory and aerodynamic heating evaluation trajectory. These conditions are used for mechanical design of rocket body.

2. Aerodynamic characteristics in flight configuration

Aerodynamic characteristics are evaluated including microprojections on the rocket surface in various flight Mach number. These values (drag coefficient, normal force coefficient, center of pressure) are applied as a baseline for orbit planning.

Fig.1:Heat flux distribution, M = 3.0, aoa = 0 deg

Publications

N/A

Computational Information

• Parallelization Methods: Process Parallelization
• Process Parallelization Methods: MPI
• Thread Parallelization Methods: n/a
• Number of Processes: 144
• Number of Threads per Process: 1
• Number of Nodes Used: 12
• Elapsed Time per Case (Hours): 8
• Number of Cases: 60

Resources Used

Total Amount of Virtual Cost(Yen): 920,262

Breakdown List by Resources

Note: Virtual Cost=amount of cost, using the unit price list of JAXA Facility Utilization program(2016)

JAXA Supercomputer System Annual Report April 2016-March 2017