Aerothermodynamic analysis for Atmospheric Entry Capsule
JAXA Supercomputer System Annual Report February 2023-January 2024
Report Number: R23EDU10300
Subject Category: Space and Astronautical Science
- Responsible Representative: Yasunori Nagata, Specially-appointed Assistant Professor, Department of Space Flight Systems
- Contact Information: Yasunori Nagata(nagata.yasunori@jaxa.jp)
- Members: Yasunori Nagata, Souta Koyama, Ritsuki Sato, Hibiki Tatsuta, Reo Iida
Abstract
In atmospheric entry capsules such as the Hayabusa sample return capsule, it is important to predict various fluid phenomena such as aerodynamic heating during the very high speed entry into the atmosphere. In this study, we are conducting thermoaerodynamic analysis of atmospheric entry capsules to understand various phenomena. Specifically, (1) prediction of the thermoaerodynamic environment of a deployable flexible aeroshell flight experimental capsule, (2) evaluation of the thermoaerodynamic environment of capsule models in expansion tube experiments, and (3) understanding of fluid phenomena related to MHD interaction effects are being conducted.
Reference URL
N/A
Reasons and benefits of using JAXA Supercomputer System
In order to properly analyze the flow around an atmospheric entry capsule in hypersonic flight, it is necessary to use a high-quality computational grid with an object-adaptive structure grid. Pointwise, which is available as ISV software, can not only generate a computational grid along an object surface, but can also flexibly adjust the computational grid, significantly reducing the time required to generate the grid. In particular, Pointwise’s powerful smoothing functions produce high-quality computational grids even for deployable flexible aeroshell capsules with complex geometries. Therefore, we decided to use ISV software. The fluid analysis was performed on our own workstation using in-house code.
Achievements of the Year
For issue (1), a two-dimensional axisymmetric fluid analysis was performed to estimate the aerodynamic heating rate to simulate the thermal environment during the flight experiment of the deployable flexible aeroshell in 2021. In particular, because of the flexibility of the aeroshell, deformation of the aeroshell caused by aerodynamic forces during atmospheric re-entry was considered (Figure 1). As a result, it was found that the shock standoff distance changes by considering the deformation, and the heat flux tends to be higher at the stagnation point and lower at the aeroshell than in the case without deformation. We will investigate an appropriate thermal environment model and reproduce the temperature data during the flight.
The ADS (Air Data System) sensor for an atmospheric entry vehicle with a deployable flexible aeroshell was also investigated using a two-dimensional axisymmetric fluid analysis (Figure 2). The ADS is a sensor that estimates vehicle attitude from the pressure difference on the wall. The fluid analysis results show that the pressure difference tends to be larger when the dynamic pressure is larger. We will investigate the ADS by performing a three-dimensional fluid analysis.
For issue (2), an expansion tube is an experimental instrument that can generate a high-speed, high-enthalpy flow and can simulate an atmospheric entry flight environment. Using this instrument, heat flux measurements have been conducted at the front and back surfaces of the Hayabusa sample return capsule model. However, since it is difficult to obtain sufficient information on the flow from the experimental measurements, we attempted to understand the phenomenon from both experimental measurements and fluid analysis. The parameters of the flow generated by the expansion tube were estimated, the flow field around the experimental model was reproduced by the fluid analysis (Figure 3), and the results were compared with the heat flux measurement results at the front and back surfaces of the model.
For issue (3), electromagnetic fluid analysis was conducted to investigate the effect of flow control technology using electromagnetic force. It was found that applying an electromagnetic force around a two-dimensional wedge shape significantly changed the shock wave shape and also affected the wall pressure distribution (Figure 4). Depending on the electromagnetic force applied, the wall pressure can increase or decrease, and a combination of both could be used to control the aerodynamic force acting on the vehicle. We will demonstrate this phenomenon through experiments and investigate its application to aerodynamic control.
Publications
– Oral Presentations
1) Hibiki Tatsuta, Kazuhiko Yamada, Yasunori Nagata, Asei Tezuka, Aerodynamic Heating Analysis of Deployable Aeroshell in RATS Reentry Flight Experiment, 54th JSASS Annual Meeting, 1D02, 2023.
2) Ritsuki Sato, Osamu Imamura, Yasunori Nagata, Kazuhiko Yamada, MHD Fluid Analysis of MHD Flow Control Effect on Hypersonic Plasma Flow Around Wedge Shape, 67th Space Sciences and Technology Conference, 3H02, 2023.
3) Souta Koyama, Yosuke Kurosaka, Kohei Shimamura, Yasunori Nagata, Kazuhiko Yamada, Hideyuki Tanno, Evaluation of SRC Full Surface Aerodynamic Heating at Super Orbital Velocity using an Expansion Tube, 67th Space Sciences and Technology Conference, 3H08, 2023.
4) Hibiki Tatsuta, Kazuhiko Yamada, Yasunori Nagata, Asei Tezuka, Aerodynamic Heating Analysis of Deployable Aeroshell with Deformation of Membrane, 67th Space Sciences and Technology Conference, 3H09, 2023.
5) Reo Iida, Tatsuro Nakao, Hitoshi Hamori, Yasunori Nagata, Kazuhiko Yamada, Jiro Kasahara, Development of Data Recovery System “RATS-2” for Sounding Rocket Experiment, Symposium on Flight Mechanics and Astrodynamics, ISAS2023-SFMA-042, 2023.
6) Souta Koyama, Kohei Shimamura, Yasunori Nagata, Kazuhiko Yamada, Hideyuki Tanno, Evaluation of SRC Frontside and Backside Aerodynamic Heating in Super Orbital Re-entry using HEK-X Expansion Tube, Symposium on Flight Mechanics and Astrodynamics, ISAS2023-SFMA-050, 2023.
7) Ritsuki Sato, Osamu Imamura, Yasunori Nagata, Kazuhiko Yamada, Study on MHD Control Effect on Hypersonic Plasma Flow around Wedge Shape, Symposium on Shock Waves, 1C3-2, 2024.
Usage of JSS
Computational Information
- Process Parallelization Methods: N/A
- Thread Parallelization Methods: N/A
- Number of Processes: 1
- Elapsed Time per Case: 1 Hour(s)
JSS3 Resources Used
Fraction of Usage in Total Resources*1(%): 0.00
Details
Please refer to System Configuration of JSS3 for the system configuration and major specifications of JSS3.
System Name | CPU Resources Used(Core x Hours) | Fraction of Usage*2(%) |
---|---|---|
TOKI-SORA | 0.00 | 0.00 |
TOKI-ST | 0.00 | 0.00 |
TOKI-GP | 0.00 | 0.00 |
TOKI-XM | 0.00 | 0.00 |
TOKI-LM | 0.00 | 0.00 |
TOKI-TST | 0.00 | 0.00 |
TOKI-TGP | 0.00 | 0.00 |
TOKI-TLM | 0.00 | 0.00 |
File System Name | Storage Assigned(GiB) | Fraction of Usage*2(%) |
---|---|---|
/home | 0.00 | 0.00 |
/data and /data2 | 0.00 | 0.00 |
/ssd | 0.00 | 0.00 |
Archiver Name | Storage Used(TiB) | Fraction of Usage*2(%) |
---|---|---|
J-SPACE | 0.00 | 0.00 |
*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.
ISV Software Licenses Used
ISV Software Licenses Used(Hours) | Fraction of Usage*2(%) | |
---|---|---|
ISV Software Licenses(Total) | 127.65 | 0.06 |
*2: Fraction of Usage:Percentage of usage relative to each resource used in one year.
JAXA Supercomputer System Annual Report February 2023-January 2024