A Study on GH2/GO2-RCS for the LOX/LH2 Integrated Propulsion/Power System
- Paper number
IAC-05-C4.P.12
- Author
Dr. Shinichiro Tokudome, Japan Aerospace Exploration Agency (JAXA)/ISAS, Japan
- Year
2005
- Abstract
The RVT team in the ISAS/JAXA is studying and developing GH2/GO2-RCS for the integration of the reusable LOX/LH2 propulsion and power system. It assumed that the GH2 and the GO2 are supplied from the liquid propellant tanks with pumps and heat-exchanging systems, which are like cryogenic evaporators (CE). The main technical problems in this study and development are as follows: cryogenic pumps for the propellants, heat exchanger for evaporating the propellants, and GH2/GO2 thruster. So far, we have started experimental study on a GH2/GO2 thruster component. The design of injector and the selection of combustion chamber material, which depend strongly on propellant mixture ratio, are the first problem to be solved. We have selected CMC material for the chamber and applied an approach to the film cooling to the design of a prototype of the injector. Result of firing test for the prototypes shows a feasibility of them.
- Abstract document