Conceptual design of the LE-7-based reusable launch systems

Masumi Nakajima, Kazuhide Mizobata, Keisuke Sawada

研究成果: Paper査読

3 被引用数 (Scopus)

抄録

Unmanned partly reusable launch systems using the LE-7 engines of Japan, modified for reuse, for the first stage and using the near-term technology are designed conceptually. Four options are considered, which are: (1) an all-rocket, two-stage system in which the rocketpowered second stage is expended, (2) an all-rocket, two-stage system in which the first stage flies back to the launch site and the rocket-powered second stage is expended, (3) a rocket-scram-jet combination, threestage system in which both the second stage using a scram-jet engine and the rocket-powered third stage are expended, and (4) a rocket-scram-jet combination, three-stage system in which the reusable second stage uses a scram-jet engine and the rocket-powered third stage is expended. The assumed mission is to deliver a 1 ton payload to LEO inclined at 52 degrees. The aerodynamic characteristics and weight estimates are made using the existing methods. It is found that the use of scram-jet engines in the second stage does not improve performance. Option 1 has the best performance, but Option 2 is more flexible. Performance of Option 2 depends mainly on the lift-todrag ratio of the first stage in the subsonic speed range.

本文言語English
DOI
出版ステータスPublished - 1998
イベント36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States
継続期間: 1998 1 121998 1 15

Other

Other36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
国/地域United States
CityReno
Period98/1/1298/1/15

ASJC Scopus subject areas

  • 工学(全般)
  • 宇宙惑星科学

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