Computational Fluid Dynamics Analysis of a Dual Mode Thruster

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...

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Bibliographic Details
Main Author: Williams, Adam N
Format: Report
Language:English
Subjects:
COMPUTATIONAL FLUID DYNAMICS
DUAL MODE
FINITE DIFFERENCE THEORY
FINITE VOLUME METHOD
Fluid Mechanics
INVISCID FLOW
Liquid Propellant Rocket Engines
MACH NUMBER
PERFORMANCE(ENGINEERING)
REACTION CONTROL SYSTEMS
SPACE SHUTTLES
STAGNATION POINT
STEADY FLOW
THESES
THREE DIMENSIONAL FLOW
THRUST CONTROL
THRUSTERS
TURBULENCE
TWO DIMENSIONAL FLOW
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Summary: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.