Curriculum Vitaes
Profile Information
- Affiliation
- Professor, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
- Degree
- Doctor of Engineering(Mar, 1996, Nagoya University)
- Contact information
- ogawa.hiroyuki
jaxa.jp - J-GLOBAL ID
- 200901051344540154
- researchmap Member ID
- 1000253790
- External link
Research on advanced thermal control systems for future scientific satellites
Based on the experience of scientific satellite projects, we analyze the current issues and future plans, and conduct research and development of advanced thermal control systems for future scientific satellites. The results of our research have been fed back to the thermal control system on board the X-ray astronomy satellite Hitomi, and are being considered for application to the next scientific satellite project.
Thermal control for scientific satellite projects
In challenging projects that actively employ thermo-fluid devices, such as the Japan-Europe Mercury mission BepiColombo, which will be exposed to extreme environments that have never been experienced before, and the large X-ray telescope satellite Hitomi, new satellite development methods that have never been experienced before are required. In such challenging projects that actively employ thermo-fluid devices, conventional satellite development methods and their extensions cannot be applied. We are contributing to the success of the project from the viewpoint of heat by leading the new research and development with our academic knowledge of thermo-fluid mechanics, such as development of new materials that can withstand extreme environments, construction of thermal design and analysis methods, development of test facilities, and development of verification methods.
Application of thermo-fluid mechanics
We are contributing to various space science project activities based on our academic knowledge of thermo-fluid and its related fields. In the research of reusable rockets, we are contributing to the solution of problems related to thermo-fluid such as engine flow, cryogenic tanks, and external flow. In the area of satellite propulsion, we have contributed to the improvement of thruster analysis technology by studying the chemical reaction flow inside hydrazine thrusters, and in the area of rocket propulsion, we have developed a method for analyzing the internal flow of solid rockets and contributed to the investigation of the causes of malfunctions in M-V rockets and SRB-A rockets. In the rocket propulsion system, he developed an internal flow analysis method for solid rockets and contributed to investigating the cause of the failure of the M-V rocket and SRB-A. He has also contributed to rocket research by working on rocket flight safety and radio frequency interference problems with rocket exhaust plumes. I have also conducted theoretical research on shock wave interference in high-speed electromagnetic fluids and propulsion systems using electromagnetic fluids.
Research Interests
8Research Areas
4Research History
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Jan, 2002 - Sep, 2003
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Apr, 1996 - Mar, 1998
Education
1Committee Memberships
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Mar, 2013 - Feb, 2015
Awards
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2015
Papers
80-
International Journal of Heat and Mass Transfer, 221 125037-125037, Apr, 2024
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Applied Thermal Engineering, 121109-121109, Jul, 2023
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Nuclear Instruments and Methods in Physics Research Section A: Accelerators, Spectrometers, Detectors and Associated Equipment, 1049 168102-168102, Apr, 2023
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Applied Thermal Engineering, 219 119573-119573, Jan, 2023A capillary pumped loop (CPL) is a capillary force-driven heat transport device that uses the phase change of a working fluid. A CPL has excellent properties in terms of heat transport capability, heat transport distance, and flexibility in heat transport path arrangement. However, its startup reliability is low, and its startup characteristics have yet to be determined. This study aims to investigate the startup characteristics of a CPL and improve its startup reliability. The startup procedures are newly proposed and experimentally verified in this paper. In the proposed method, the evaporator was preheated in addition to the reservoir preheating before startup. Verification was done by switching the order of the reservoir preheating and evaporator preheating. The experimental results showed that the proposed methods enable the CPL to start up even in conditions where the CPL was unable to start up by a conventional method (reservoir temperatures ranging from 40 °C to 80 °C). It was also confirmed that the order of the evaporator preheating and reservoir preheating affects the degree of overshoot of the evaporator temperature. The maximum temperature of the evaporator at the startup was reduced by up to 91.5 °C in case the evaporator was preheated before the reservoir preheating.
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JOURNAL OF SPACECRAFT AND ROCKETS, Feb, 2022Typically, spacecraft development is costly and time-consuming because of the many iterations usually needed to reach optimal design solutions. This paper presents an innovative approach that eliminates the need to iterate the thermal design process using a network of variable conductance oscillating heat pipes (VC-OHPs) on every structural panel. The temperatures of the panels where components are mounted would thus be maintained at constant levels by VC-OHPs, even if the instruments' locations or heat dissipation changes. A structural thermal model was built to verify the proposed thermal and structural design in a simulated deep space environment and in a launch environment. It consisted of two VC-OHPs and six aluminum honeycomb panels. A thermal vacuum test was conducted to demonstrate the temperature control by the VC-OHPs. The test results showed that temperature control by VC-OHPs could maintain the panels operating as evaporators at stable temperatures and follow the reservoir temperature. A vibration test was conducted under the launch environment of a Japanese H2A rocket. The results confirmed that the structural thermal model met requirements for resistance to mechanical launch environment. The VC-OHPs functioned after the vibration test. The structural thermal model showed that the proposed thermal control architecture is feasible in an actual spacecraft in terms of thermal and structure design.
Misc.
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42nd International Conference on Environmental Systems, Jul, 2012 Lead author
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42nd International Conference on Environmental Systems, Jul, 2012 Lead author
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Proceedings of the International Astronautical Congress, IAC, 11 8842-8847, 2012A new reusable sounding rocket is proposed (1) to reduce operation costs from that of existing expendable sounding rockets and (2) to provide frequent launch opportunities. This paper describes the current status of the conceptual design of the reusable sounding rocket, including system concept, mission profile and system configuration. Some of the R&D status is also presented. Copyright © (2012) by the International Astronautical Federation.
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42nd International Conference on Environmental Systems 2012, ICES 2012, 2012The inflation and peel-off characteristics of a multilayer insulation (MLI) blanket under a depressurization environment have been evaluated for establishing a JAXA design standard. The venting conductance of gas flow from inside to the outside of MLI was evaluated in a steady state test, and was confirmed to take a value of the same level regardless of shape or size or pressure level when having the same perforation, spacer type, and attachment specification. In the depressurization test, MLI was observed as not inflating in a region of higher pressure even at higher depressurization speed, while inflating in a lower pressure region. The differential pressure between the inside and outside of MLI peaks when the level of pressure drops to about one kilo pascal or less. In addition, a simple mathmatical model of MLI inflation and venting is constructed and numerical simulations based on the model are conducted, which indicate that depressurization ratio (depressurization speed per the level of pressure) and volume of MLI are the dominantparameters. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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Meeting Abstracts of the Physical Society of Japan, 67(1) 139-139, 2012
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Meeting Abstracts of the Physical Society of Japan, 67(1) 140-140, 2012
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41st International Conference on Environmental Systems, AIAA-2011-518, Jul, 2011 Lead author
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火薬学会秋季研究発表講演会講演要旨集, 2011, 2011
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Meeting Abstracts of the Physical Society of Japan, 66(1) 122-122, 2011
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Meeting Abstracts of the Physical Society of Japan, 66(2) 113-113, 2011
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20TH ESA SYMPOSIUM ON EUROPEAN ROCKET AND BALLOON PROGRAMMES AND RELATED RESEARCH, 700 137-142, 2011A fully reusable sounding rocket is proposed in ISAS/JAXA. Vehicle systems and ground / flight operations are conceptually designed for observations of atmospheric phenomena, micro-gravity experiments and so on. The present design of the reusable sounding rocket is summarized. In phase A in the proposed reusable sounding rocket project, technical demonstrations for key technologies to develop the reusable sounding rocket are planed as follows; 1) reusable engine development and repeated engine operation development, 2) reusable insulation development for cryogenic tank, 3) aerodynamic design and flight demonstration for returning flight, 4) fuel/oxidizer management demonstration, 5) landing gear development and 6) health management system construction.
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Proceedings of National Heat Transfer Symposium, 48th 93-93, 2011 Peer-reviewed
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SPACE TELESCOPES AND INSTRUMENTATION 2010: ULTRAVIOLET TO GAMMA RAY, 7732, Oct 24, 2010The joint JAXA/NASA ASTRO-H mission is the sixth in a series of highly successful X-ray missions initiated by the Institute of Space and Astronautical Science (ISAS). ASTRO-H will investigate the physics of the high-energy universe by performing high-resolution, high-throughput spectroscopy with moderate angular resolution. ASTRO-H covers very wide energy range from 0.3 keV to 600 keV. ASTRO-H allows a combination of wide band X-ray spectroscopy (5-80 keV) provided by multilayer coating, focusing hard X-ray mirrors and hard X-ray imaging detectors, and high energy-resolution soft X-ray spectroscopy (0.3-12 keV) provided by thin-foil X-ray optics and a micro-calorimeter array. The mission will also carry an X-ray CCD camera as a focal plane detector for a soft X-ray telescope (0.4-12 keV) and a non-focusing soft gamma-ray detector (40-600 keV) . The micro-calorimeter system is developed by an international collaboration led by ISAS/JAXA and NASA. The simultaneous broad bandpass, coupled with high spectral resolution of Delta E ~7 eV provided by the micro-calorimeter will enable a wide variety of important science themes to be pursued.
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40th International Conference on Environmental Systems, AIAA-2010-6056, Jul, 2010
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40th International Conference on Environmental Systems, AIAA-2010-6089, Jul, 2010
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Conference Record of the IEEE Photovoltaic Specialists Conference, 1112-1117, 2010 Peer-reviewedThe Japan Aerospace Exploration Agency has been developing the Mercury Magnetospheric Orbiter (MMO), which is Japanese part of the BepiColombo mission. During its mission around Mercury, the spacecraft will be exposed to high solar irradiance of up to 11 suns, with an estimated maximum solar panel temperature of 230°C. In such an environment, solar cells are required to operate under high intensity and high temperature (HIHT) conditions. Therefore, it is necessary to evaluate the durability of solar cells to meet the power requirements throughout the mission life. We conducted a continuous operation test under HIHT conditions to examine the validity of the solar array configuration, using the interior planetary thermal vacuum chamber. Our HIHT tests clarified the following facts: (i) Transparency of the coverglass and the performance of the solar cells do not degrade and (ii) transparency of the DC93-500 adhesive in the top cell response region degrades mainly due to ultraviolet exposure at high temperatures. We decided to use AR0213 coverglass (from JDSU) with a thickness of 300 μm, which have a longer cut-on wavelength in ultraviolet region. With this configuration, the predicted decrease in Pmax due to the HIHT environment is 17.3% and that due to radiation effects is 11.0% Our new design will offer the available power at EOL of 394.2 W, which is 46.7 W greater than the required power. © 2010 IEEE.
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40th International Conference on Environmental Systems, ICES 2010, 2010 Peer-reviewedThis paper reports development of an experimental small LHP with PTFE wick. PTFE porous materials with 0.8 - 2.2 μm pore radius were fabricated and the basic properties were evaluated. An experimental small LHP with the PTFE wicks was designed and tested in an atmospheric condition. A PTFE wick with 1.2 μm pore radius was used to demonstrate the loop performance. The test results showed excellent operating characteristics of the LHP. © 2010 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
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INTERNATIONAL JOURNAL OF ENERGETIC MATERIALS AND CHEMICAL PROPULSION, 9(3) 219-231, 2010Hydroxylammonium nitrate (HAN) based liquid propellant has been investigated as a candidate for the monopropellant to be utilized in the reaction control system of satellites as an alternative to hydrazine. This propellant, which consists of ammonium nitrate, methanol, and water, has moderate burning characteristics, sufficiently low freezing temperature, high density, low toxicity, and its density x Isp is 70% higher than hydrazine. In a previous study, the combustion characteristics of the propellants were obtained and found to be very complex. In this paper, the research was focused on the combustion characteristics of HAN aqueous solution. Sample solutions of several concentrations, 95-50 mass %, were prepared. The measurement of linear burning rates, the temperature measurement of the combustion wave, and the observation of combustion phenomena were included in the study. The linear burning rate does not increase monotonically with increasing HAN concentration. The burning rates increase as the HAN concentration increases up to 80 mass %, and decrease as the concentration increases from 80 to 95 mass %. The burning rate peaks at around 80 mass % of HAN concentration. The combustion mode is very complex and is dependent upon composition and pressure. Temperature measurements indicate that the role of the two-phase region is very important, and the boiling of water caused by superheat is responsible for the high burning rate. The relationship between the rate of nucleation of bubbles and the linear burning rate is discussed.
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61st International Astronautical Congress 2010, IAC 2010, 6 5076-5093, 2010ISAS activities for reusable rocket technology and architecture including flight demonstration by the RVT (Reusable Vehicle Testing) have shown various progresses in technical areas such as frequent-flight propulsion systems, reusable rocket engines, returning flight and vertical landing techniques and demonstrations, composite cryogenic LH2 tank studies, new architectures for reusable and repeated flights with quick turnaround and so on. Following these basic studies of reusable rocket, mission definition and system requirement synthesis of the reusable sounding rocket are completed. In addition to the technical and performance related issues, its operational aspects and requirements for the frequent and repeated flight were given stressed. Throughout the studies, technical readiness to the reusable rocket technique and for the system synthesis for the reusable sounding rocket vehicle are in progress. For the sounding rocket's system definition and requirement analysis, research of the flight demand such as the number-of-flight per year and its frequency by the potential user communities. These requirements are from the needs of the middle to upper atmosphere research, studies from micro-gravity community, engineering community which may use this repeated flight opportunity. Copyright ©2010 by the International Astronautical Federation. All rights reserved.
Books and Other Publications
1Presentations
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46th International Conference on Environmental Systems, Jul, 2016
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第16回宇宙科学シンポジウム 講演集 = Proceedings of the 16th Space Science Symposium, Jan, 2016, 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)第16回宇宙科学シンポジウム (2016年1月6日-7日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)相模原キャンパス), 相模原市, 神奈川県資料番号: SA6000046247レポート番号: S4-010
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45th International Conference on Environmental Systems, Jul, 2015
Professional Memberships
5-
Sep, 2020
Research Projects
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科学研究費助成事業, 日本学術振興会, Apr, 2023 - Mar, 2027
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科学研究費助成事業, 日本学術振興会, Apr, 2023 - Mar, 2026
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B), Japan Society for the Promotion of Science, Apr, 2018 - Mar, 2021
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Grants-in-Aid for Scientific Research Grant-in-Aid for Challenging Exploratory Research, Japan Society for the Promotion of Science, Apr, 2016 - Mar, 2018
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Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (C), Japan Society for the Promotion of Science, 2008 - 2010
Industrial Property Rights
6Academic Activities
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Panel moderator, Session chair, etc., Peer reviewJul, 2003 - Present
● 指導学生等の数
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Fiscal Year2018年度(FY2018)Doctoral program1
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Fiscal Year2019年度(FY2019)Doctoral program2Master’s program1JSPS Research Fellowship (Young Scientists)1
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Fiscal Year2020年度(FY2020)Doctoral program1Master’s program1JSPS Research Fellowship (Young Scientists)1
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Fiscal Year2018年度(FY2018)Doctoral program1
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Fiscal Year2019年度(FY2019)Doctoral program2Master’s program1JSPS Research Fellowship (Young Scientists)1
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Fiscal Year2020年度(FY2020)Doctoral program1Master’s program1JSPS Research Fellowship (Young Scientists)1
● 専任大学名
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Affiliation (university)東京大学（University of Tokyo)
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Affiliation (university)東京大学（University of Tokyo)
● 所属する所内委員会
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ISAS Committee研究所会議
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ISAS Committeeプログラム会議
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ISAS Committee信頼性品質会議
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ISAS Committee環境・安全管理統括委員会
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ISAS CommitteeISASニュース編集小委員会
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ISAS Committee宇宙科学プログラム技術委員会
