著者
苅田 丈士 片野 克哉 緒川 修治
出版者
一般社団法人 日本機械学会
雑誌
年次大会 2020 (ISSN:24242667)
巻号頁・発行日
pp.J19108, 2020 (Released:2021-03-25)

Pulse detonation engine (PDE) performances were calculated. Simple relationships were derived for detonation, exhausting and ventilation to calculate the engine performances. Calculated Isp were about 20 km/s in subsonic flight and 5 km/s in supersonic flight, respectively. A spaceship with PDE and a rocket engine was conceptually designed, and its transportation performance was estimated with use of the extended Tsiolkovskii method. When the mass at take-off was 3,000 kg, 2,230 kg was carried to the altitude of 101 km.