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Optimisation of solid rocket motor blast tube and nozzle assemblies using computational fluid dynamics
Author(s)
Scholtz, Kelly Burchell
Date Issued
2017
Type
Thesis
Publisher
Cape Peninsula University of Technology
Abstract
A framework for optimising a tactical solid rocket motor nozzle is established and investigated
within the ANSYS Workbench environment. Simulated results are validated
against thrust measurements from the static bench firing of a full-scale rocket. Grid independence
is checked and achieved using inflation based meshing. A rocket nozzle contour
is parametrized using multiple control points along a spline contour. The design of experiments
table is populated by a central composite design method and the resulting response
surfaces are used to find a thrust optimised rocket nozzle geometry. CFD results are based
on Favre-mass averaged Navier-Stokes equations with turbulence closure implemented with
the Menter SST model. Two optimisation algorithms (Shifted Hammersley Sampling and
Nonlinear Programming by Quadratic Lagrangian) are used to establish viable candidates
for maximum thrust. Comparisons are made with a circular arc, Rao parabolic approximation
and conical nozzle geometries including the CFD simulation there-off. The effect
of nozzle length on thrust is simulated and optimised within the framework. Results generally
show increased thrust as well as demonstrating the framework's potential for further
investigations into nozzle geometry optimisation and off-design point characterisation.
within the ANSYS Workbench environment. Simulated results are validated
against thrust measurements from the static bench firing of a full-scale rocket. Grid independence
is checked and achieved using inflation based meshing. A rocket nozzle contour
is parametrized using multiple control points along a spline contour. The design of experiments
table is populated by a central composite design method and the resulting response
surfaces are used to find a thrust optimised rocket nozzle geometry. CFD results are based
on Favre-mass averaged Navier-Stokes equations with turbulence closure implemented with
the Menter SST model. Two optimisation algorithms (Shifted Hammersley Sampling and
Nonlinear Programming by Quadratic Lagrangian) are used to establish viable candidates
for maximum thrust. Comparisons are made with a circular arc, Rao parabolic approximation
and conical nozzle geometries including the CFD simulation there-off. The effect
of nozzle length on thrust is simulated and optimised within the framework. Results generally
show increased thrust as well as demonstrating the framework's potential for further
investigations into nozzle geometry optimisation and off-design point characterisation.
Additional information
Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2017.
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203104846-Scholtz-Kelly-Burchell-Mtech-Mechanical-Engineering-Eng-2017.pdf
Description
Thesis
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