Physical Simulation in Space Launcher Engine Risk Assessment

Abstract: ã 2010 IEEE. Personal use of this material is permitted. However, permission to reprint/republish this material for advertising or promotional purposes or for creating new collective works for resale or redistribution to servers or lists, or to reuse any copyrighted component of this work in other works must first be obtained from the IEEE. This paper describes the application of physics based simulation techniques to the risk analysis and risk informed design of liquid propellant rocket engines used on space launch vehicles. Understanding the operational and failure behavior of crewed space launcher propulsion systems is critical to the characterization of integrated vehicle risk. The analysis of threats posed by the failure of these systems to the mission, vehicle and crew is informed by a study of off nominal behavior. To better answer questions on the failure behavior of rocket engines, it is essential to study the underlying physics. To this end, the development of simulation tools to aid the risk analyst in the study of system level behavior is elucidated. ROCETS (ROCket Engine Transient Simulator) simulation code was used to investigate the steady state and transient physical behavior of cryogenic rocket engines for nominal and off-nominal operating conditions. Insights obtained from the application of this methodology are discussed.

Keywords: RAMS 2010 Proceedings - Product Reliability - Risk Assessment

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