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Aircraft gust alleviation technology

JAXA Supercomputer System Annual Report April 2016-March 2017

Report Number: R16E0031

  • Responsible Representative: Kazutoshi Ishikawa(Aeronautical Technology Directorate, Next Generation Aeronautical Innovation Hub Center)
  • Contact Information: Kenichi Saitoh(ksaitoh@chofu.jaxa.jp)
  • Members: Kenichi Saitoh, Hamidreza Kheirandish
  • Subject Category: Aviation(Aircraft)

Abstract

In the research and development of aircraft gust alleviation technology, we aim to reduce the accident in the cabin hit by clear air turbulence. To suppress such an aircraft motion, we are developing a control technology using LIDAR which detects the turbulence. Currently, we are verifying the theory by the wind tunnel test.

Goal

Please refer 'R&D of onboard safety avionics technology to prevent turbulence-induced aircraft accidents (SafeAvio) | STAR – Safety Technology for Aviation and Disaster-Relief Program | Aeronautical Technology Directorate'.

Objective

Please refer 'R&D of onboard safety avionics technology to prevent turbulence-induced aircraft accidents (SafeAvio) | STAR – Safety Technology for Aviation and Disaster-Relief Program | Aeronautical Technology Directorate'.

References and Links

Please refer 'R&D of onboard safety avionics technology to prevent turbulence-induced aircraft accidents (SafeAvio) | STAR – Safety Technology for Aviation and Disaster-Relief Program | Aeronautical Technology Directorate'.

Use of the Supercomputer

JSS is used for an estimation of a stability derivative of a wind tunnel model.

Necessity of the Supercomputer

CFD analysis is used to obtain stability derivative coefficients, if there is an unknown phenomenon observed. System design and its verification based on the simulation will be necessary in the future because the wind tunnel test is difficult and expensive.

Achievements of the Year

A grid of the half model with three control surfaces was generated. (Fig.1).

An example of the result is shown in Fig. 2.

Boundary layer of the wind tunnel wall can be simulated by the grid. (Fig. 3)

Annual Reoprt Figures for 2016

Fig.1:Grid for analysis

 

Annual Reoprt Figures for 2016

Fig.2:Sample of pressure distribution

 

Annual Reoprt Figures for 2016

Fig.3:Sample of boundary layer of wind tunnel

 

Publications

N/A

Computational Information

  • Parallelization Methods: Process Parallelization,Serial
  • Process Parallelization Methods: MPI
  • Thread Parallelization Methods: n/a
  • Number of Processes: 96
  • Number of Threads per Process: 1
  • Number of Nodes Used: 3
  • Elapsed Time per Case (Hours): 4.5, 5
  • Number of Cases: 30, 220-330

Resources Used

 

Total Amount of Virtual Cost(Yen): 60,963

 

Breakdown List by Resources

Computational Resources
System Name Amount of Core Time(core x hours) Virtual Cost(Yen)
SORA-MA 9,828.75 16,165
SORA-PP 3,743.15 31,959
SORA-LM 363.32 8,174
SORA-TPP 0.00 0

 

SORA-FS File System Resources
File System Name Storage assigned(GiB) Virtual Cost(Yen)
/home 3.97 13
/data 562.03 1,899
/ltmp 813.80 2,750

 

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)

JAXA Supercomputer System Annual Report April 2016-March 2017


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Location

Chofu Aerospace Center
7-44-1 Jindaiji Higashi-machi, Chofu-shi, Tokyo