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Nonlinear Modeling and Control of a Propellant MixerA mixing chamber used in rocket engine combustion testing at NASA Stennis Space Center is modeled by a second order nonlinear MIMO system. The mixer is used to condition the thermodynamic properties of cryogenic liquid propellant by controlled injection of the same substance in the gaseous phase. The three inputs of the mixer are the positions of the valves regulating the liquid and gas flows at the inlets, and the position of the exit valve regulating the flow of conditioned propellant. The outputs to be tracked and/or regulated are mixer internal pressure, exit mass flow, and exit temperature. The outputs must conform to test specifications dictated by the type of rocket engine or component being tested downstream of the mixer. Feedback linearization is used to achieve tracking and regulation of the outputs. It is shown that the system is minimum-phase provided certain conditions on the parameters are satisfied. The conditions are shown to have physical interpretation.
Document ID
20040008331
Acquisition Source
Stennis Space Center
Document Type
Preprint (Draft being sent to journal)
Authors
Barbieri, Enrique (Houston Univ. TX, United States)
Richter, Hanz (NASA Stennis Space Center Stennis Space Center, MS, United States)
Figueroa, Fernando (NASA Stennis Space Center Stennis Space Center, MS, United States)
Date Acquired
September 7, 2013
Publication Date
June 1, 2003
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
SE-2002-08-00056-SSC
Meeting Information
Meeting: 2003 American Control Conference
Location: Denver, CO
Country: United States
Start Date: June 4, 2003
End Date: June 6, 2003
Funding Number(s)
CONTRACT_GRANT: NAS13-98033
CONTRACT_GRANT: NASW-99027
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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