A spacecraft is exposed to various thermal-fluid environments from the time of launch to the period in space and return to the Earth. Understanding of thermal and aerodynamic characteristics in re-entry to the atmosphere is essential especially in the development of the next-generation space transportation systems. In this study, we study the methods to estimate the aerodynamic heating by using functional molecule sensors, and study and develop thermal-fluid measurement technology which can be used to measure extreme environment fields with high temperatures (1000°C and higher) as well as cryogenic temperatures. For the next-generation spacecraft which is to carry out missions over long periods under extreme thermal environments, it is essential that they have thermal control systems capable of exhausting heat from the internal devices using the limited electricity and weight resources. This laboratory, therefore, tries to address this demand and bring about a breakthrough in a realization of next-generation spacecraft missions through our research and development of loop heat pipes (LHPs) and oscillating heat pipes (OHPs) as light-weight and space-saving/non-electric heat transport devices.

　【Scope of Research】

1. Elucidation of Aerodynamic Characteristics and Aerodynamic Heating in Atmospheric Re-entry
2. Development of Next-Generation Thermal Control Devices and Systems Enabling Spacecraft to Explore Safely and Sustainably
3. Development of New System Using Fluid Force for Exploration in Planet Having Atmosphere

　【Fundamental Technology for Accompanishment of Research】

４．Visualizaition and Mesurement Technique in Ultimate Environment

These researches are not individual but interactive and complementary. Our objective is developing this research field as "Thermal and Fluid Systems Field in Aerospace Engineering".