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
Thermal Design
,Thermal Control
,熱工学
,プラズマ理工学
,航空宇宙工学
,Thermal Engineering
,Plasma Science and Technology
,Aeronautics
Research Areas
Aerospace, marine, and maritime Engineering / Aerospace engineering /
Manufacturing technology (mechanical, electrical/electronic, chemical engineering) / Thermal engineering /
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 12(29) To_4_1-To_4_10 2014
The thermal condition of ASTRO-H under air-cooled environment before launch is investigated with a thermal testing and a computational analysis. The thermal testing shows that the temperatures of devices are confirmed to be within the operating ra...
Advances in the Astronautical Sciences 146 697-702 2013
A fully reusable sounding rocket is proposed and conceptually designed in ISAS/JAXA. In phase A in the proposed project, technical demonstrations for key technologies to develop the reusable sounding rocket are planed as follows; 1) reusable engin...
A fully reusable sounding rocket is proposed and conceptually designed in ISAS/JAXA. In phase A in the proposed project, technical demonstrations for key technologies to develop the reusable sounding rocket are planed as follows; 1) reusable engin...
Science and technology of energetic materials : Journal of the Japan Explosives Society 73(5) 169-174 Dec 2012
In order to understand the effect of the CH4/O-2 chemical kinetic models. for detonation phenomena, the numerical calculations use one detailed chemical kinetic model k311 and four reduced chemical kinetic models such as DRG30 model, DRG23 model, ...
42nd International Conference on Environmental Systems 2012, ICES 2012 2012 [Refereed]
A thermal control system (TCS) of a microsatellite is proposed with loop heat pipes (LHPs) including bypass valves. "Free from restrictions in thermal design," all instruments can be mounted anywhere on the internal side of the six structure panel...