Liquid Oxygen/Liquid Methane Integrated Propulsion System Test Bed

Abstract

In support of NASA's former Propulsion and Cryogenic Advanced Development (PCAD) project, a liquid oxygen (LO 2 )/liquid methane (LCH 4 ) Integrated Propulsion System Test Bed (IPSTB) was conceived, designed, and advanced to the Critical Design Review (CDR) stage at the Johnson Space Center. The IPSTB's primary objective is to study LO 2 /LCH 4 propulsion system steady state and transient performance, operational characteristics and to validate computer models of a LO2/LCH4 propulsion system for use in future flight design work.The baseline configuration was designed to accommodate one 6,050 lbf main engine, four 100 lbf reaction control engines (RCE's), and several cold flow simulators providing flow rates representative of 25 to 200 lbf thrusters. The IPSTB feed system includes four ground based, spherical propellants tanks capable of supporting up to 240 seconds of main engine firing and simultaneous RCE profiles, four RCE pods housing the RCE engines and simulators, and a Thermodynamic Vent System (TVS) for thermal conditioning of the lines and tanks. Additionally, a liquid nitrogen/liquid methane heat exchanger, to be used in conjunction with the TVS and aerogel insulation, were planned to give the system the capability to deliver densified/sub-cooled cryogenic methane to the engine inlets. Two phase thermal and dynamic fluid flow models of the IPSTB were built to predict the system performance characteristics under a variety of operating modes and to aid in the overall system design work. While at ambient temperature and simulated altitude conditions at the White Sands Test Facility, the IPSTB and its approximately 600 channels of system instrumentation would be operated to perform a variety of integrated main engine and RCE hot fire tests. The pressure, temperature, and flow rate data collected during this testing would then be used to validate the analytical models of the IPSTB's https://ntrs.nasa.gov/search.jsp?R=20110012829 2018-05-10T15:42:53+00:00Z thermal and dynamic fluid flow performance. An overview of the IPSTB design and analytical model development will be presented. In support of NASA's Propulsion and Cryogenic Advanced Development (PCAD) project, a liquid oxygen (LO 2 )/liquid methane (LCH 4 ) Integrated Propulsion System Test Bed (IPSTB) was designed and advanced to the Critical Design Review (CDR) stage at the Johnson Space Center. The IPSTB's primary objectives are to study LO 2 /LCH 4 propulsion system steady state and transient performance, operational characteristics and to validate fluid and thermal models of a LO2/LCH4 propulsion system for use in future flight design work. Two phase thermal and dynamic fluid flow models of the IPSTB were built to predict the system performance characteristics under a variety of operating modes and to aid in the overall system design work. While at ambient temperature and simulated altitude conditions at the White Sands Test Facility, the IPSTB and its approximately 600 channels of system instrumentation would be operated to perform a variety of inte...

Characterization of a Pressure-Fed LOX/LCH4 Reaction Control System Under Simulated Altitude and Thermal Vacuum Conditions

“…A follow-on effort to develop an article more appropriately sized for testing was conceived of in the Integrated Propulsion Systems Test Bed. 4 This effort was intended to focus more on integrated system operating characteristics and serve as an anchor to validate fluid and thermal models; however it was cancelled after CDR when the PCAD project ended with the Constellation Program.…”