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Adaptation Of A Control System To Varying Missile ConfigurationsEkinci, Ozgur 01 December 2009 (has links) (PDF)
Varying missile configurations may create uncertainty for a missile control algorithm developed with linear control theory, for instance the control system performance requirements may not be satisfied anymore. Missile configuration may change during the missile design period due to variations in subsystem locations, subsystem weights and missile geometry. Likewise, burning propellant, deployment of aerodynamic surfaces and wings with varying sweep angle can be considered as in-flight missile configuration changes. This thesis study addresses development and analysis of an adaptive missile control algorithm to account for the uncertain effects caused by varying missile configuration.
Control algorithms, designed using pole placement, are augmented with adaptive neural networks. The resulting controller is a type of model reference adaptive controller. Adaptation characteristics of the augmented control algorithms are investigated to changing center of pressure location and missile geometry. Analyses are performed for three different missile configurations using simulation.
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Launch vehicle performance enhancement using aerodynamic assistMcDavid, Brian Robert, Hartfield, Roy J., January 2008 (has links) (PDF)
Thesis (M.S.)--Auburn University, 2008. / Abstract. Vita. Includes bibliographical references (p. 49-53).
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Investigation of the flow turning loss in unstable solid propellant rocket motorsMatta, Lawrence Mark 12 1900 (has links)
No description available.
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Characterization of mechanical properties of advanced polymeric systems evaluated for a cryotank environmentPavlick, Matthew Michael 05 1900 (has links)
No description available.
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Experimental and numerical study of a hydrogen peroxide / hydroxyl terminated polybutadiene hybrid rocket /Farbar, Erin January 1900 (has links)
Thesis (M.App.Sc.) - Carleton University, 2006. / Includes bibliographical references (p. 163-172). Also available in electronic format on the Internet.
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Techniques to Assess Acoustic-Structure Interaction in Liquid Rocket EnginesDavis, R. Benjamin January 2008 (has links)
Thesis (Ph. D.)--Duke University, 2008. / Includes bibliographical references.
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3-D flow and performance of a tandem-bladed rocket pump inducer /Excoffon, Tony. January 1992 (has links)
Thesis (M.S.)--Virginia Polytechnic Institute and State University, 1992. / Vita. Abstract. Includes bibliographical references (leaves 111-113). Also available via the Internet.
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Development of a solid hydrogen particle generator for feasibility testing of a solid hydrogen optical mass gauging systemAdams, Thomas Edgar. Van Sciver, Steven W. January 2004 (has links)
Thesis (M.S.)--Florida State University, 2004. / Advisor: Dr. Steven Van Sciver, Florida State University, College of Engineering, Department of Mechanical Engineering. Title and description from dissertation home page (viewed Sept. 23, 2004). Includes bibliographical references.
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Simulations of a sub-scale liquid rocket engine transient heat transfer in a real gas environment /Masquelet, Matthieu M. January 2006 (has links)
Thesis (M. S.)--Aerospace Engineering, Georgia Institute of Technology, 2007. / Ruffin, Stephen, Committee Member ; Seitzman, Jerry, Committee Member ; Menon, Suresh, Committee Chair.
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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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