Spelling suggestions: "subject:"pockets (aeronautics) -- nozzles"" "subject:"pockets (aeronautics) -- nozzle's""
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Experimental analysis of plug nozzlesBalasaygun, Eray, 1941- January 1964 (has links)
No description available.
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Experimental determination of three-dimensional liquid rocket nozzle admittancesBell, William Alvin 08 1900 (has links)
No description available.
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The effect of nozzle nonlinearities on the nonlinear stability of liquid rocket motorsPadmanabhan, Mysore Srikantiah 12 1900 (has links)
No description available.
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Wake closure conditions in plug nozzle flowfields /Lang, Derek Edward. January 1999 (has links)
Thesis (Ph. D.)--University of Washington, 1999. / Vita. Includes bibliographical references (leaves 132-140).
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Damping of axial instabilities by solid propellant rocket exhaust nozzlesJanardan, Bangalore Ananthamurthy 08 1900 (has links)
No description available.
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Two-dimensional, compressible time-dependent nozzle flowSheppard, Richard Roy 08 1900 (has links)
No description available.
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Flow study of the nozzle region of the space shuttle solid rocket motorSquire, Daniel E. 12 April 2010 (has links)
A flow visualization study was conducted to analyze flow characteristics inside the solid rocket motor (SRM) used on the NASA space shuttle. The objective of this investigation was to determine whether the internal flow structure could adversely affect the nozzle/case joint and the surrounding casing. Also, it was hoped to learn more about causes of low level acoustic pressure oscillations observed during SRM test firings.
The SRM was simulated by water flow through a plexiglas model mounted in a water tunnel. Dye and hydrogen bubble visualization techniques along with hot water analysis methods were used to detect flow patterns. Visual results recorded on video tape indicated strong circumferential and recirculation flows around the nozzle.
Vortex formation near the nozzle inlet was also observed and was the prime focus of this investigation. Because the nozzle inlet geometry was very similar to an aircraft engine inlet operating close to the ground, vortices seen in this investigation were believed to behave like vortices seen around engine inlets. Based on the results from this investigation and the results of previous engine inlet vortex studies, it was concluded that the nozzle vortices could be the excitation source of SRM pressure oscillations. / Master of Science
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Numerical simulation of the structural response of a composite rocket nozzle during the ignition transient.Pitot de la Beaujardiere, Jean-Francois Philippe. January 2009 (has links)
The following dissertation describes an investigation of the structural response behaviour of a
composite solid rocket motor nozzle subjected to thermal and pressure loading during the motor
ignition period, derived on the basis of a multidisciplinary numerical simulation approach. To
provide quantitative and qualitative context to the results obtained, comparisons were made to
the predicted aerothermostructural response of the nozzle over the entire motor burn period.
The study considered two nozzle designs – an exploratory nozzle design used to establish the
basic simulation methodology, and a prototype nozzle design that was employed as the primary
subject for numerical experimentation work. Both designs were developed according to
fundamental solid rocket motor nozzle design principles as non-vectoring nozzles for
deployment in medium sized solid rocket booster motors. The designs feature extensive use of
spatially reinforced carbon-carbon composites for thermostructural components, complemented
by carbon-phenolic composites for thermal insulation and steel for the motor attachment substructures. All numerical simulations were conducted using the ADINA multiphysics finite element
analysis code with respect to axisymmetric computational domains. Thermal and structural
models were developed to simulate the structural response of the exploratory nozzle design in
reference to the instantaneous application of pressure and thermal loading conditions derived
from literature. Ignition and burn period response results were obtained for both quasi-static and
dynamic analysis regimes.
For the case of the prototype nozzle design, a flow model was specifically developed to simulate
the flow of the exhaust gas stream within the nozzle, for the provision of transient and steady
loading data to the associated thermal and structural models. This arrangement allowed for a
more realistic representation of the interaction between the fluid, thermal and structural fields
concerned. Results were once again obtained for short and long term scenarios with respect to
quasi-static and dynamic interpretations. In addition, the aeroelastic interaction occurring
between the nozzle and flow field during motor ignition was examined in detail. The results obtained in the present study provided significant indications with respect to a
variety of response characteristics associated with the motor ignition period, including the
magnitude and distribution of the displacement and stress responses, the importance of inertial
effects in response computations, the stress response contributions made by thermal and pressure
loading, the effect of loading condition quality, and the bearing of the rate of ignition on the calculated stress response.
Through comparisons between the response behaviour predicted during the motor ignition and
burn periods, the significance of considering the ignition period as a qualification and
optimisation criterion in the design of characteristically similar solid rocket motor nozzles was established. / Thesis (M.Sc.Eng.)-University of KwaZulu-Natal, Durban, 2009.
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Optimisation of solid rocket motor blast tube and nozzle assemblies using computational fluid dynamicsScholtz, Kelly Burchell January 2017 (has links)
Thesis (MTech (Mechanical Engineering))--Cape Peninsula University of Technology, 2017. / 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.
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