Experimental research on key technologies for future launcher propulsion

The Institute of Flight Propulsion, together with ASTRIUM Space Transportation, have set up a test facility to investigate key technologies of main stage engine design in the preface of future launcher propulsion development. The test bed is operated with kerosene and gaseous oxygen (GOX). Aim of the program is to . investigate key parameters for future TCA development on a laboratory scale level and at an early stage of the development process. For the different objectives and the wide range of operational conditions the test bench offers several setups: To test materials with respect to their oxidation resistance in an ORCC gas generator, a heat sink combustion chamber of 35mm diameter with staged combustion has been developed, manufactured and qualified. To investigate the characteristics of different injector element designs, spray tests in an optical accessible chamber are conducted followed by first hot fire tests in a heat sink-single element thrust chamber. A modular water cooled thrust chamber is used for a more detailed analysis of combustion efficiency, heat release and heat transfer to the cooled wall. The thrust chamber also provides hot gas at a wide operational pressure and mixture ratio envelope for qualification testing of CMC material samples and integral CMC structures. Aim of this paper is to give an overview over past, present and future research activities.