A5061419287- Rocket and propulsion systems research
- Fluid Dynamics and Heat Transfer
- Electrohydrodynamics and Fluid Dynamics
- Heat Transfer and Boiling Studies
- Energetic Materials and Combustion
- Modular Robots and Swarm Intelligence
- Spacecraft and Cryogenic Technologies
- Ionosphere and magnetosphere dynamics
- Laser-Plasma Interactions and Diagnostics
- Advanced Sensor and Energy Harvesting Materials
- Heat Transfer Mechanisms
- Heat transfer and supercritical fluids
- Magnetic confinement fusion research
- Fluid Dynamics and Turbulent Flows
- Innovative Energy Harvesting Technologies
- Nuclear Engineering Thermal-Hydraulics
Kyoto University
1995-2023
Kyoto University of Education
2023
Kobe University
2003
The liquid film cooling technique was employed in bipropellant thrusters to protect the thrust chamber from high-temperature combustion gases. Heat soak-back throat face plate occurs interval between each pulse firing event. A jet would be injected onto superheated wall operation. To gain experimental knowledge for contributing effective and hazard prevention of thrusters, pulsed tests metal plate, which a intermittently surface, were conducted. behavior captured by high-speed camera,...
AbstractRadial transport is controlled by DC and RF in the HIEI tandem mirror. H-mode-like behavior limiter biasing created through formation of radial electric field sheared rotation. In case with enhanced axial confinement, high-β plasma(β ~ 14%) attained. Injection non-resonant reduces peak value central cell density broadens profile, which leads to reduction heat load onto end plate.
In a bipropellant thruster, part of the liquid fuel is injected onto combustion chamber wall to form film, which protect from gases. Particularly in pulse operation, heated with temperature gradient formed by heat soak back nozzle throat. this study, transient processes film formation and distribution were visualized high-speed imaging an infrared camera, respectively. The behavior wetting front propagation transfer characteristic analyzed found that mass flow rate was important factor for...
This paper aims at proposing a piezoelectric generator for self-powered system by vibration energy regenaration. In order to demonstrate the effectiveness of proposed design method, numerical simulation and laboratory experiment will be done using cantilever beam model equipped with 4 surface bonded PZT tiles pairs.
In a bipropellant thruster, part of the liquid fuel is injected onto combustion chamber wall to form film, which protect from gases. Particularly in pulse operation, heated with temperature gradient formed by heat soak back nozzle throat. this study, transient processes film formation and distribution were visualized using high-speed camera an infrared camera, respectively, for pulsed injection jet on surface gradient. As result analysis, knowledge about behavior during cooling no-cooling...