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OMV/VTE variable thrust engine analysisThe objective of the present work is to develop a predictive CFD based analytical tool for the variable thrust engine (VTE) in the orbital maneuvering vehicle (OMV). This objective is being accomplished within the framework of the Los Alamos KIVA computer code for chemically reactive flows with sprays. For the OMV application, the main structure of KIVA is to be retained while reformulating many of the phenomenological submodels, enhancing some of the numerics, and adding more features. The analytical model consists of the general conservation equations for two phase reactive flows and of submodels for turbulence, chemical reactions, and bipropellant sprays. Tailoring this model to the OMV engine brings about the added complexities of combustion and flow processes that occur in a liquid hypergolic propellant rocket chamber. This report exposes the foundation upon which the analytical tool is being constructed and developed. Results from a cursory computational exercise involving the simulation of the flow and combustion processes in a hypothetical N2H4/N2O4 rocket engine thrust chamber is presented and discussed.
Document ID
19960022965
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Larosillere, Louis
(NASA Marshall Space Flight Center Huntsville, AL United States)
Litchford, Ron
(Tennessee Univ. Space Inst. Tullahoma, TN United States)
Jeng, San-Mou
(Tennessee Univ. Space Inst. Tullahoma, TN United States)
Date Acquired
August 17, 2013
Publication Date
October 26, 1989
Publication Information
Publication: Overview of the Center for Advanced Space Propulsion
Subject Category
Spacecraft Propulsion And Power
Accession Number
96N71336
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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