Systems Analysis of a LOX/LH2 Rocket Engine with a Transpiration-Cooled Ceramic Thrust-Chamber

Kurzfassung

This paper discusses various different applications of transpiration cooled ceramic thrust chambers. The paper concentrates on medium to high thrust cryogenic propellant (i.e. liquid hydrogen / liquid oxygen) rocket engines. A systems study with a parametric variation of engine- and material specifications (such as chamber pressure, mixture ratio, wall heat conductivity etc.) is performed. Achievable benefits, such as the reduction of weight and manufacturing cost, as well as an increased reliability and higher lifetime due to thermal cycle stability are discussed.