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Distributed Parameter Analysis of Pressure and Flow Disturbances in Rocket Propellant Feed SystemsA digital distributed parameter model for computing the dynamic response of propellant feed systems is formulated. The analytical approach used is an application of the wave-plan method of analyzing unsteady flow. Nonlinear effects are included. The model takes into account locally high compliances at the pump inlet and at the injector dome region. Examples of the calculated transient and steady-state periodic responses of a simple hypothetical propellant feed system to several types of disturbances are presented. Included are flow disturbances originating from longitudinal structural motion, gimbaling, throttling, and combustion-chamber coupling. The analytical method can be employed for analyzing developmental hardware and offers a flexible tool for the calculation of unsteady flow in these systems.
Document ID
19660023040
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Dorsch, Robert G. (NASA Lewis Research Center Cleveland, OH, United States)
Wood, Don J. (Kentucky Univ. Lexington, KY, United States)
Lightner, Charlene (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1966
Subject Category
Propulsion Systems
Report/Patent Number
E3122
NASA-TN-D-3529
Accession Number
66N32330
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
UNSTEADY FLOW
DYNAMIC RESPONSE
FEED SYSTEM
MATHEMATICAL MODEL

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