Turbo-Hybrid-Rocket Propulsion for Small Launch Vehicle Operations

CFDRC, in conjunction with support from Orbital Sciences, Allison Advanced Development Corporation and NASA Ames Research Center proposes a novel Turbo-Hybrid Rocket (THR) for the first stage of a responsive and cost-effective small launch vehicle system. This work will leverage CFDRC's extensive experience and leadership in tactical missile ATR technology and NASA Ames breakthroughs in hybrid rocket fuel research to conceive an air-breathing booster engine that could revolutionize small launch vehicle propulsion. During Phase I a comprehensive assessment of THR performance in small launch vehicle applications will be completed. Two key enabling technology issues to be focused upon during Phase I will be (1) an overall system analysis layout assessment and (2) combustion performance of a NASA Ames paraffin fuel in a turbo hybrid rocket afterburner installation. A technology risk mitigation plan that addresses rationale and test exit criteria for both a small scale engine and full scale afterburner demonstration will be prepared. In addition, a sub-orbital design analysis of the THR concept will be conducted in the Orbital Sciences Pegasus SLV or an appropriate equivalent. Preliminary mission-performance assessment, launch response and cost/benefit tradeoffs will be completed. The ultimate result of this effort will be definition of a THR propulsion system capable of answering the Air Force's need to rapidly, flexibly, and cheaply place small satellites into low earth orbit.