Conceptual Study of Rocket Powered TSTO with Fly-back Booster

A conceptual analysis of various rocket powered full reusable two-stage-to-orbit launch vehicle is performed. A vertical take off and horizontal landing vehicle, whose booster flies back to launch site, is considered. A LOX/LH2 rocket engine is used as the main propulsion system. The present and near-term technology level is assumed for the propulsion system and materials. In this study, several concepts are investigated under the unified conceptual design process. The comparisons between these concepts are performed taking into considerations the gross lift off mass of the vehicle. In particular, a parametric study of the mass allocation between the booster and orbiter is performed. Ideal velocity increment of the booster is used as a control parameter of the mass allocation. Both powered fly-back and glideback booster concepts are included in the parametric study. Furthermore, CH4, Kerosene and densified LOX/LH2 by supercooling are considered as propellants. An omission of powered flyback equipments from booster is also examined. Finally, the influence of the payload mass and payload-bay length upon the payload mass fraction is discussed.