| Budget Amount *help |
¥43,810,000 (Direct Cost: ¥33,700,000、Indirect Cost: ¥10,110,000)
Fiscal Year 2021: ¥8,190,000 (Direct Cost: ¥6,300,000、Indirect Cost: ¥1,890,000)
Fiscal Year 2020: ¥13,000,000 (Direct Cost: ¥10,000,000、Indirect Cost: ¥3,000,000)
Fiscal Year 2019: ¥9,490,000 (Direct Cost: ¥7,300,000、Indirect Cost: ¥2,190,000)
Fiscal Year 2018: ¥13,130,000 (Direct Cost: ¥10,100,000、Indirect Cost: ¥3,030,000)
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| Outline of Final Research Achievements |
In this study, by assuming a 120-200-seater, one-aisle narrow-body aircraft which corresponds to B737, the design of an electric propulsion system for the aircraft with a total thrust of 20 MW was studied. The propulsion system consisted of a superconducting generator / motor / cable, a gas turbine, an inverter, and a cooling device. The superconducting propulsion system was cooled with subcool liquid nitrogen. The fuel was liquid hydrogen, and this cold heat was used to cool the superconducting system. First, the transport characteristics and AC loss properties of REBCO superconducting tapes were actually measured. Applying our original low AC loss reduction and enhancement current capacity technique, we carried out numerical analysis to find the optimum structure of fully superconducting rotary machines for aircraft. Furthermore, the feasibility of the entire system such as energy and heat balance was verified.
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