Conceptual design of two-stage reusable launch systems using X-33

Keisuke Sawada, Masaharu Takashi

Research output: Contribution to conferencePaper

2 Citations (Scopus)

Abstract

A conceptual design of a rocket-based two-stage partially reusable launch system is first explored. For the first stage, the X-33 experimental hypersonic vehicle is assumed as a realistic candidate of a rocket-based vehicle. The second stage is assumed to be expendable, which inserts 1-ton payload into low Earth orbit. Although several optimistic assumptions are made, we have found three sets of solutions for various orbital inclination angles. The payload to takeoff weight ratio of the resulting partially reusable launch system is found to be about 0.7%. In addition, a rocket-based two-stage fully reusable system is also explored by assuming the X-33 as the second stage and the VentureStar as the first stage. A payload of 6 ton into LEO is found possible. The payload to takeoff weight ratio for this configuration becomes slightly better than 0.5%.

Original languageEnglish
Publication statusPublished - 2001 Dec 1
Event10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001 - Kyoto, Japan
Duration: 2001 Apr 242001 Apr 27

Other

Other10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001
CountryJapan
CityKyoto
Period01/4/2401/4/27

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering
  • Control and Systems Engineering

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    Sawada, K., & Takashi, M. (2001). Conceptual design of two-stage reusable launch systems using X-33. Paper presented at 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference 2001, Kyoto, Japan.