research on space propulsion flow dynamics

Report Number：R17EU0802 Subject Category：Space and Astronautical Science

URL：https://www.jss.jaxa.jp/ar/e2017/4480/

Responsible Representative

Eiichi Sato, Department of Space Flight Systems, Institute of Space and Astronautical Science

Contact Information

Tomoki Matsuno [email protected]

Members

Toru Shimada, Mikiro Motoe, Tomoki Matsuno, Goutham Karthikeyan, Akiyo Takahashi

Abstract

It is natural and logical to require safe and economic space transportation for the realization of sustainably growing future space economy. However, the current space transportation system cannot be as safe as the current aircraft because the current rocket has essential explosive nature of the propellant.

In order to realize non-explosive safe rocket, we suggest A-SOFT hybrid rocket and research on computer simulation of swirling turbulent combustion field and combustion oscillation in hybrid rocket engine for realization of this type of rocket.

Safety evaluation of hybrid rocket with numerical analysis is also conducted.

Reasons for using of JSS2

It is impossible to conduct practical numerical analysis for turbulent combustion phenomena with general computer from the perspective of computing speed and memory capacity. Therefore high speed and large scale analysis with super computer is necessary for development of hybrid rocket.

Achievements of the Year

In order to understand the influence of the ratio of axial-to-tangential oxidizer mass flow rate on the internal combustion flow field of A-SOFT, unsteady combustion turbulent flow analysis is conducted on 2 cases of A-SOFT hybrid rocket. Their difference is only axial-to-tangential oxidizer mass flow rate. POD analysis is also applied to the simulation results. Fig. 1 shows the comparison of instantaneous eddy structure. Through this simulation, the difference of engine performance and internal combustion field are observed.

In order to establish scheme of unsteady combustion simulation for hybrid rocket, Detached-eddy simulation (DES) have been conducted to the rocket and its results are compared with results of Large-

Research on Space Propulsion Flow Dynamics

JAXA Supercomputer System Annual Report April 2017-March 2018

eddy Simulation (LES). Fig.2 shows numerical estimations and an experimental result of axial distribution of fuel regression rate of swirling-oxidizer-flow-type hybrid rocket (numerical estimations are instantaneous value). Fig.3 shows contours of temperature that are obtained from LES and DES. These result show that both methods can conduct reasonable simulation for such kind of hybrid rocket.

Numerical analysis on the combustion stability characteristics of hybrid rocket (HR) motors was conducted in order to study the HR intrinsic low-frequency instability. Through the unsteady computational fluid dynamics simulation, we were able to model the phenomenon (Fig. 4) and parametrically analyze it.

We studied about safety of space transportation from the view of resilience engineering which is new method of system safety engineering, and we showed that adoption of boundary layer combustion type hybrid rocket has the possibility of contributing safely. To show the possibility quantitatively, we constructed a mathematical model including CFD program to evaluate damage of blast of hybrid rocket propellant.

Fig.1 Eddy structure in the A-SOFT hybrid rocket motor


Fig.2 Axial distribution of fuel regression rate(instantaneous)

Fig.3 Contour of temperature

Fig.4 Temporal variation of pressure monitored at midpoint of the combustion chamber


Publications

Non Peer-reviewd papers 1) Takahashi, A., Shimada, T., "Essentially Non-explosive propulsion Paving a Way for Fail-Safe Space

Transportation," TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN, ISTS Special Issue, Vol.16(2018), No.1, pp.1-8.

Presentations 1) M. Motoe, T. Matsuno and T. Shimada, "Numerical Analysis of Combustion Field in Hybrid Rocket

Motor with Swirling and Axial Oxidizer Injection", 7th EUCASS, July 3-6, 2017, Milan, Italy. 2) T. Shimada, T. Matsuno, K. Obata, G. Karthkeyan, and M. Motoe. "Evaluation of Non-steady

Combustion Characteristics of Tangential-Axial Injection Hybrid Rocket by Large Eddy Simulation." Fourteenth ICFD, November 1-3, 2017, Sendai, Japan.

3) T. Matsuno, M. Motoe, K. Obata, N. Kimura, K. Kitagawa and T. Shimada, "Swirling Combustion Flow Field Evaluation of Tangential-Axial Injection Hybrid Rocket by Large Eddy Simulation", 9th AJCPP, March 14-17, 2017, Xiamen, China.

4) Mikiro Motoe, "Delayed Detached Eddy Simulation of Combustive Flows in a Swirling-Oxidizer-Flow-Type Hybrid Rocket", 31st ISTS, June 3-9, 2017, Matsuyama, Japan.

5) Karthikeyan, Goutham, and Toru Shimada. "Parametric Analysis of Combustion Instability in Axial-Injected Hybrid Rocket Motors using Computational Fluid Dynamics", 53rd AIAA/SAE/ASEE Joint Propulsion Conference, July 10-12, 2017, Atlanta, USA.

6) Karthikeyan, Goutham, and Toru Shimada. "Validation of numerical prediction of hybrid rocket combustion instability", Fourteenth ICFD, November 1-3, 2017, Sendai, Japan.

7) Takahashi, A., Shiamda, T., "Resilience Engineering of Space Transportation," Mechanical Engineering Congress, 2017 Japan, 9/5, Saitama (in Japanese).

8) Takahashi, A., Shimada, T., "Essentially Non-explosive propulsion Paving a Way for Fail-Safe Space Transportation," 31st International Symposium on Space Technology and Science, Matsuyama, 2017.6.3-6.9.

9) Takahashi, A., Shimada, T., "Evaluation of Energy for Detonation Occurrence of Space Propulsion System", Asia Pacific Symposium on Safety 2017, Fukuoka, 2017/12/1.


Usage of JSS2

Computational Information

Resources Used

Fraction of Usage in Total Resources*1 (%): 0.86

Details Computing Resources

System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 7,097,640.17 0.94 SORA-PP 23,131.03 0.29 SORA-LM 96.01 0.05 SORA-TPP 0.00 0.00

File System Resources

File System Name Storage assigned(GiB) Fraction of Usage*2 (%) /home 1,573.97 1.09 /data 10,971.31 0.20 /ltmp 8,641.10 0.65

Archiver Resources

Archiver System Name Storage used(TiB) Fraction of Usage*2 (%) J-SPACE 6.29 0.27

*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

Parallelization Methods MPI Thread Parallelization Methods N/A Number of Processes 90 Elapsed Time per Case 3,600.00 hours






Contact Information

Kazuma Emoto [email protected]

Members

Hitoshi Kuninaka, Yoshinori Takao, Kazuma Emoto

Abstract

For manned space exploration, space radiation causes harsh radiation exposure. To protect crews from radiation exposure, we propose radiation shielding using planetary magnetic fields. We evaluate the magnetic shielding by numerical simulation because the planetary magnetic field expands the large area. We simulate space radiation in the planetary magnetic field and clarify the performance of the magnetic shielding.


We need large-scale parallel computing to simulate trajectories of many energetic particles.


We focus on Martian magnetic anomalies and conducted the simulation of the radiation shielding. We simulated trajectories of energetic particles using a relativistic Buneman-Brois method and evaluated the radiation shielding using the magnetic anomaly. Figure 1 shows a distribution of normalized particle hits reaching the Martian surface. The magnetic anomaly could completely shield energetic particles with a specific incident angle. The complete shielding means that the radiation exposure is zero on the Martian surface. Martian magnetic anomalies could realize the radiation shielding from energetic particles.

Numerical investigation of radiation shielding using planetary magnetic fields


Fig.1 A distribution of normalized particle hits

Publications

Peer-reviewed papers 1) Kazuma Emoto, Yoshinori Takao, and Hitoshi Kuninaka: A Preliminary Study on Radiation

Shielding Using Martian Magnetic Anomalies, Biological Sciences in Space, in press. Presentations 1) Kazuma Emoto, Yoshinori Takao, and Hitoshi Kuninaka: A Preliminary Investigation on Radiation

Shielding Using Martian Magnetic Anomalies, Space Transportation Symposium FY2017, STEP-2017-021, Sagamihara, January 2018.


Usage of JSS2


Resources Used



System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 329,457.50 0.04 SORA-PP 0.00 0.00 SORA-LM 0.00 0.00 SORA-TPP 0.00 0.00


File System Name Storage assigned(GiB) Fraction of Usage*2 (%) /home 014.31 0.01 /data 143.05 0.00 /ltmp 2,929.69 0.22

Archiver Resources




Parallelization Methods MPI Thread Parallelization Methods N/A Number of Processes 3020 Elapsed Time per Case 4.00 hours





Eiichi Sato, Institute of Space and Astronautical Science

Contact Information

Akira Oyama [email protected]

Members

Akira Oyama, Dong Lee, Hiroaki Fukumoto, Takuya Harada, Hiroaki Nakano, Takara Watanabe, Shota Inoue, Risako Aoki, Shigetaka Kawai, Satoshi Sekimoto, Shun Tamura, Srikanth Surendranath, Daiki Terakado, Yuta Ozawa, Satoshi Shimomura, Taku Nonomura

Abstract

We conduct fundamental research on aerodynamics such as aerodynamic acoustic noise generated by supersonic jet and aerodynamic design of Mars aircraft.


Large eddy simulation is required for analysis of aeroacoustics generated from a supersonic jet. Aerodynamic design of Mars airplane requires several hundred cases of CFD computation. Therefore, a supercomputer is necessary.


Aerodynamic airfoil design optimization of flying-wing-type Mars airplane has been conducted. The result show that there is a tradeoff between maximizing lift to drag ratio and improving stability performance. A guideline for airfoil shape design has been also obtained. We also conducted uncertainty quantification of aerodynamic performance of an airfoil in low Reynolds number flow condition.

Study of high speed fluid


Fig.1 Aerodynamic airfoil design optimization of flying-type Mars airplane

Fig.2 Uncertainty quantification of airfoil performance in low Reynolds number flow


Publications

Non peer-reviewed papers 1) Takuya Harada, Koji Fujita, Akira Oyama, Hiroya Mamori, Makoto Yamamoto, Aerodynamic

Design of Airfoil for Flying Wing Mars Airplane, AIAA Scitech, Kissimmee, FL, US, Jan 8-12. 2018 2) Shigetaka Kawai, Thijs Bouwhuis, Yoshiaki Abe, Aiko Yakeno, Taku Nonomura, Akira Oyama,

Harry Hoeijmakers, and Kozo Fujii, Investigation of Maximum Velocity Induced by Body-Force Fields for Simpler Modeling of Plasma Actuators, AIAA Aerospace Sciences Meeting, AIAA Science and Technology Forum and Exposition 2018, Kissimmee, FL, US, Jan 8-12. 2018

3) Hiroaki Fukumoto, Hikaru Aono, Taku Nonomura, Akira Oyama and Kozo Fujii, Large-Eddy Simulations of Flow Control Effects of a DBD Plasma Actuator at Various Burst Frequencies on a Dynamic Floweld around a Pitching NACA0012 Airfoil at Reynolds Number of 256,000, AIAA Aerospace Sciences Meeting, AIAA Science and Technology Forum and Exposition 2018, Kissimmee, FL, US, Jan 8-12. 2018.


Usage of JSS2


Resources Used



System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 14,918,585.64 1.97 SORA-PP 1,596.63 0.02 SORA-LM 0.00 0.00 SORA-TPP 0.00 0.00


File System Name Storage assigned(GiB) Fraction of Usage*2 (%) /home 3,621.92 2.51 /data 86,487.83 1.60 /ltmp 18,013.20 1.36

Archiver Resources




Parallelization Methods parametric study. Thread Parallelization Methods OpenMP Number of Processes 52 Elapsed Time per Case 16.00 hours






Contact Information

Ikkoh Funaki [email protected]

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.


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


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.

Numerical Simulation of Advanced Spacecraft Propulsion


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


Resources Used



System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 64,935.21 0.01 SORA-PP 36,403.88 0.46 SORA-LM 0.00 0.00 SORA-TPP 0.00 0.00



Archiver Resources




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





Masaki Fujimoto, Department of Solar Sciences, ISAS

Contact Information

Toshifumi Shimizu [email protected]

Members

Toshifumi Shimizu, Yusuke Kawabata, Takahiro Hasegawa, Tamafumi Doi, Yumi Bamba

Abstract

The purpose of this project is to physically understand the mechanisms responsible for the occurrence of solar flares. The Hinode satellite has been accurately measuring magnetic fields spatially distributed at the solar surface. Using maps of the measured magnetic fields, we infer 3D magnetic field structures in the solar corona by performing 3D magnetohydrodynamics simulations. With 3D magnetic field structures derived from the simulations, we promote studies for exploring physical mechanisms involved in the occurrence of solar flares.


We perform 3D magnetohydrodynamics numerical simulations by using vector magnetic field data acquired with the Hinode satellite in order to infer 3D magnetic field structures in the corona. We need large computational resource in order to perform three-dimensional magnetohydrodynamics simulations.


Nonlinear force-free field (NLFFF) modeling is a useful tool to infer the three-dimensional magnetic fields in the solar corona, where the force-free approximation is valid. If we give the magnetic field observed at the solar surface as a boundary condition, we can solve this nonlinear equation. However, the NLFFF modeling is known to have some uncertainties. We investigate one of the uncertainties; Initial condition dependency. Usually, NLFFF calculation starts from potential field. In our study, we used liner force-free field(LFFF) and investigated how the NLFFF solutions are affected by the initial condition. We found that the total magnetic energy and free energy is independent from the initial condition (Fig.1), although the shape of the field lines are different among each solution (Fig.2). While the difference of the shape of the field lines is small in the lower atmosphere, it becomes larger in the

NLFFF calculation of the solar coronal magnetic field based on Hinode observations


heigher region. This is because the field lines in the lower atmosphere is affected by the bottom boundary and tends to be independent from the initial condition.

Fig.1 Magnetic energy of the initial condition (blue), NLFFF(red), and free energy(green,

the difference between NLFFF and potential field)


Fig.2 Comparison between X-ray image obtained with Hinode and field lines

derived from NLFFF.

Publications

Peer-reviewed papers 1) Y. Kawabata, S. Inoue, and T. Shimizu, "Non-potential Field Formation in the X-shaped

Quadrupole Magnetic Field Configuration", The Astrophysical Journal, 842, 106, 2017 Presentations 1) Y. Kawabata, A. Asensio Ramos, S. Inoue, T. Shimizu:"Comparison between chromospheric field

derived from He I 10830 A observation and nonlinear force-free field modeling from photosphere", ASJ meeting, Hokkaido University, September 2017.

2) Takahiro Hasegawa, Toshifumi Shimizu: "Reversed Rotation of a Sunspot Associated with the X2.1 flare in NOAA 12297", Daiwa-Adrian Workshop, London, UK, July 2017.

3) Takahiro Hasegawa, Toshifumi Shimizu: "Reversed rotation of a sunspot and large-scale flare", ASJ meeting, Hokkaido University, September 2017.

4) Takahiro Hasegawa, Toshifumi Shimizu, "Reversed Rotation of the Well-Developed Sunspot Associated with an X-class Flare", Helicity Thinkshop, Tokyo, November, 2017

5) Takahiro Hasegawa, Toshifumi Shimizu:"Observational studies on magnetic helicity associated with solar flares", 25th Hinode-Laboratory Plasma meeting, Tokyo University, February, 2018


Other 1) Takahiro Hasegawa: "Observational Studies on Magnetic Helicity Associated with Solar Flares",

Master thesis, The University of Tokyo, March 2018.

Usage of JSS2


Resources Used



System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 0.00 0.00 SORA-PP 62,736.30 0.79 SORA-LM 0.00 0.00 SORA-TPP 84,134.72 9.39



Archiver Resources









Kazuyuki Miho, ISAS Program Office

Contact Information

Kazuhiko Yamada [email protected]

Members

Kazuhiko Yamada, Yusuke Higo, Kazuki Nohara, Tomoya Kazama

Abstract

Hayabusa' is the first sample return mission to an asteroid in deep space and proved its significance worldwide. The sample return mission will become one of the important missions in future planetary exploration. A sample return capsule is indispensable technology to realize it. The objectives of this activity are to take over its heritage and to enhance its technology in order to realize the flexible and attractive future sample return mission.


Computational fluid dynamics related the sample return capsule was carried out using super computer. These results will be reflected in the design of future sample return capsules. It is generally difficult to reproduce the fluid dynamic condition in free flight of sample return capsule in ground tests. The numerical simulation is useful to understand the fluid dynamics phenomenon. However, the numerical simulation related to fluid dynamics requires the large computational resource. So, the super computer is indispensable. Its complex fluid dynamics around the sample return capsule can be understood, combining the results of both ground tests and numerical analyses using a super computer.


In this year, the numerical fluid analysis was carried out, focused on the wake flow field of Hayabusa-type sample return capsule using the numerical code with Baldwin-Lomax turbulence model (Fig.1). A wake flow field is important information for the design of the parachute deployment method and for the evaluation of the aerodynamic instability. In this study, the effect of the flow conditions including an angle of attach and an uniform velocity on the wake flow field was investigated (Fig.2). Additionally, these numerical results were compared with experimental results, that is visualized wake flow in low

Research and Development of Sample Return Capsule for future planetary exploration


speed wind tunnel by PIV method in order to confirm the validity of the adopted numerical analysis method (Fig.3). In the future, this numerical code and method will be utilized for the development of the aerodynamics database to the future sample return capsule design and for the evaluation of aerodynamic performance.

Fig.1 Computational grid

Fig.2 Flow field around the Hayabusa-type sample return capsule in the case of vairious angle of attacks.


Fig.3 Comparison between CFD results and wind tunnle results about velocity profile in wake flow

Publications

Presentations 1) Kazuki Nohara, "Numerical simulation and flow visualization of wake flow field of Hayabusa-Type

sample return capsule",Symposium on Flight Mechanics and Astrodynamics: 2017, sagamihara.


Usage of JSS2


Resources Used



System Name Amount of Core Time (core x hours) Fraction of Usage*2 (%) SORA-MA 80,382.74 0.01 SORA-PP 15.28 0.00 SORA-LM 0.00 0.00 SORA-TPP 0.00 0.00



Archiver Resources






research on space propulsion flow dynamics

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