ADAPTATION REQUIREMENTS OF THE EJ200 AS A DRY HYDROGEN FLY BACK ENGINE IN A REUSABLE LAUNCHER STAGE

摘要

This paper describes the adaptation requirements for the of the EJ-200 military turbofan engine to make it the fly-back propulsion system of a partially reusable space transportation system. In a first step, the present design status of the Liquid Fly-back Booster (LFBB) is summarized, characteristic size and load data are listed, and the benefits of switching the turbofan propellants from kerosene to hydrogen are explained. The main part of the paper is devoted to checking all major EJ-200 components for their compatibility with the new application and propellant.