Computational fluid dynamics analysis of a dual mode thruster
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Authors
Williams, Adam N.
Subjects
Computational Fluid Dynamics
Dual Mode Thruster
Underexpanded Flow
Barrel Shock
Mach Disk
Finite Difference Method
Finite Volume Method
Dual Mode Thruster
Underexpanded Flow
Barrel Shock
Mach Disk
Finite Difference Method
Finite Volume Method
Advisors
Hobson, Garth V.
Date of Issue
1999-09
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Current objectives at NASA Johnson Space Center ate directed at future upgrade and replacement of the U.S. Space Shuttle's, currently toxic, Reaction Control System thrusters with dual mode thrusters that use nontoxic propellants. Experimentation to determine any performance advantages obtained using a dual mode thruster has not been performed by NASA. A computational fluid dynamics analysis is performed to evaluate the internal flow characteristics of this thruster under low thrust mode, torch igniter only, conditions. Several computational models, both two- and three-dimensional, are constructed to simulate the internal, steady-state flow characteristics. Comparison is made with current data on a similar type of flow (highly underexpanded free-jet flow) to show the appearance of barrel shocks and Mach disks. Regions of stagnate flow where heat transfer to chamber surfaces will be high and engine thrust performance are predicted based on computational data. Two different flow solvers, one using a finite volume method and the other using a finite difference method, are used to predict the engine's performance. A comparison of the two flow solvers is given based on their relative performance to compute solutions to this problem
Type
Thesis
Description
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Format
xiv, 138 p.;28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.