Study of Space Transportation Technology (Integrated Design of Airframe and Engine)

JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0073

Responsible Representative: Koichi Okita(Research and Development Directorate, Unit IV)
Contact Information: Susumu Hasegawa(hasegawa.susumu@jaxa.jp)
Members: Takeshi Kanda
Subject Category: Space(Rocket,Rocket engine,Space transportation)

Abstract

Integrated design technology of Spaceplane and its engine for future space transportation is studied, and conceptual design technology will be established. Wind tunnel tests, CFD simulation and conceptual study for estimation of transportation ability are conducted. The spaceplanes have larger thrust and larger engines than the planes have. Therefore, aerodynamic characteristics of the spaceplanes interacts with the engine thrust and the engine integration. In the study, stability is a key issue, as well as the transportation ability and economical efficiency.

Goal

Establishment of integrated design technology of spaceplane and its engine for future space transportation.

Objective

Establishment of integrated design method of airframe and its engine of spaceplane in aerodynamics and their integration.

References and Links

N/A

Use of the Supercomputer

Pre calculation is conducted for wind tunnel tests, and the calculated results are used for discussion on the test results. After certification of the CFD results by the test data, simulation calculation is conducted for other conditions, too.

Necessity of the Supercomputer

Numbers, conditions and measured data of the wind tunnels are limited, so CFD simulation is necessary. Especially, 3D flow simulation needs fast calculation with large memory. It can be conducted only with a supercomputer.

Achievements of the Year

Pre-calculation of the test model was conducted for preparation of the wind tunnel tests, and the calculation results are used for discussion on the experimental tests. Some calculated results agreed with the experimental ones, and others are not. The established CFD simulation procedure will be used to improve configurations and operating conditions of the spaceplane and its engines.

Fig.1:Distribution of pressure coefficient around the wind tunnel test model. Mach number is 1.1.

Publications

Presentations

1) Susumu Hasegawa, Takeshi Kanda,’Preliminary Numerical Simulation of Flow around Spaceplane for Airframe Engine Integration’, ISTS 31th, Matsuyama, Japan, Jun 9, 2017.

Computational Information

Parallelization Methods: Process Parallelization
Process Parallelization Methods: MPI
Thread Parallelization Methods: n/a
Number of Processes: 128
Number of Threads per Process: 1
Number of Nodes Used: 4
Elapsed Time per Case (Hours): 256
Number of Cases: 60

Resources Used

Total Amount of Virtual Cost(Yen): 23,211

Breakdown List by Resources

Computational Resources
System Name	Amount of Core Time(core x hours)	Virtual Cost(Yen)
SORA-MA	0.00	0
SORA-PP	716.45	6,117
SORA-LM	0.00	0
SORA-TPP	0.00	0

SORA-FS File System Resources
File System Name	Storage assigned(GiB)	Virtual Cost(Yen)
/home	9.54	79
/data	95.37	792
/ltmp	1,953.13	16,223

J-SPACE Archiving System Resources
Archiving System Name	Storage used(TiB)	Virtual Cost(Yen)
J-SPACE	0.00	0

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