Advanced Rocket Propulsion Systems for Reusable Ballistic Single-Stage-to-Orbit Vehicles BETA and Delta-Clipper.

Abstract

A single-stage-to-orbit VTOVL mission was evaluated using four different types of mixed-mode propulsion systems such as dual engines, dual mixture ratio, dual position nozzle and dual throat. VTOVL laucheners using staged combustion and gas-generator cycle engines. The single stage launcher BETA-II was taken as reference vehicle. Hydrogen and/or hydrocarbons as fuels with oxygen were used as propellants. A constant payload mass transported into low earth orbit was assumed, and the minimal effective net mass of the launcher was determined. Optimizations and variations were made for the effective net mass of the BETA-vehicle versus mixture ratios and chamber pressures.