Rocket Engine Combustion Devices Design and Demonstration Program

摘要

This report describes work accomplished in the Rocket Engine Combustion Devices Design and Demonstration (RECDD&D) Program. It was part of the overall Advanced Launch System (ALS) Program, later redesignated the National Launch System (NLS). The objectives of the ALS Combustion Devices ADP were to demonstrate design and manufacturing technologies which would maximize component reliability while minimizing the cost of fabricating those components. In response, the ALS program was initiated with the goal of developing new, low cost 580 klb thrust class Space Transportation Main Engine (STME), and a 640 klb thrust class Space Transportation Booster Engine (STBE). The STME would use liquid hydrogen as the fuel while the STBE would use liquid methane. Both would use liquid oxygen as the oxidizer. In May of 1989 Rocketdyne started work on the contract to design, fabricate, and test two liquid hydrogen thrust chamber and gas generator assemblies. The thrust chamber included an injector, combustion chamber, nozzle and ignition system. These components were to demonstrate the basic reliability, operability, and cost objectives of the NLS program. This report documents the results achieved on that contract.