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Prediction of pressure and flow transients in a gaseous bipropellant reaction control rocket engineAn analytic model is developed to predict pressure and flow transients in a gaseous hydrogen-oxygen reaction control rocket engine feed system. The one-dimensional equations of momentum and continuity are reduced by the method of characteristics from partial derivatives to a set of total derivatives which describe the state properties along the feedline. System components, e.g., valves, manifolds, and injectors are represented by pseudo steady-state relations at discrete junctions in the system. Solutions were effected by a FORTRAN IV program on an IBM 360/65. The results indicate the relative effect of manifold volume, combustion lag time, feedline pressure fluctuations, propellant temperature, and feedline length on the chamber pressure transient. The analytical combustion model is verified by good correlation between predicted and observed chamber pressure transients. The developed model enables a rocket designer to vary the design parameters analytically to obtain stable combustion for a particular mode of operation which is prescribed by mission objectives.
Document ID
19740062132
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Markowsky, J. J.
(American Electric Power Service Corp. New York, N.Y., United States)
Mcmanus, H. N., Jr.
(Cornell University Ithaca, N.Y., United States)
Date Acquired
August 7, 2013
Publication Date
August 1, 1974
Publication Information
Publication: Computers and Fluids
Volume: 2
Subject Category
Propulsion Systems
Accession Number
74A44882
Funding Number(s)
CONTRACT_GRANT: NGR-33-010-070
Distribution Limits
Public
Copyright
Other

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