Development of electric propulsion systems for aircrafts
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- Iwakuma Masataka
- Principal Investigator
- 九州大学
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- 川越 明史
- Co-Investigator
- 鹿児島大学
About this project
- Japan Grant Number
- JP18H03783
- Funding Program
- Grants-in-Aid for Scientific Research
- Funding organization
- Japan Society for the Promotion of Science
- Project/Area Number
- 18H03783
- Research Category
- Grant-in-Aid for Scientific Research (A)
- Allocation Type
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- Single-year Grants
- Review Section / Research Field
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- Medium-sized Section 21:Electrical and electronic engineering and related fields
- Research Institution
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- Kyushu University
- Project Period (FY)
- 2018-04-01 〜 2022-03-31
- Project Status
- Completed
- Budget Amount*help
- 43,810,000 Yen (Direct Cost: 33,700,000 Yen Indirect Cost: 10,110,000 Yen)
Research Abstract
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.
Details 詳細情報について
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- CRID
- 1040000781994103552
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- Text Lang
- ja
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- Data Source
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- KAKEN