WorldCat Identities

GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING

Overview
Works: 131 works in 169 publications in 1 language and 173 library holdings
Classifications: QA911,
Publication Timeline
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Most widely held works by GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
Solid Propellant Admittance Measurements by the Driven Tube Method by B.T Zinn( Book )

4 editions published between 1974 and 1977 in English and held by 4 WorldCat member libraries worldwide

The progress made during the fourth year of an investigation for the measurement of the response of a burning solid propellant to flow disturbances is presented. In this study a modification of the impedance tube technique is used to measure the response over a wide frequency range. Further refinements in the data reduction computer program are discussed. Anomalous behavior for high pressure (300 psig) tests which shows that the propellant sample periodically drives and damps acoustic oscillations during a burn was resolved. Techniques for improving the accuracy of the measured data and the quality of the burn have been developed. Testing will resume during the next year. (Author)
Combustion Generated Noise in Turbopropulsion Systems( Book )

3 editions published between 1973 and 1975 in English and held by 3 WorldCat member libraries worldwide

The results are presented of a three year program investigating direct combustion noise in hydrocarbon-air flames. Tasks completed during the final year of the program have been (1) the use of an exterior facility to investigate the noise from a large, 2 inch diameter burner and (2) the use of the anechoic facility to test flames stabilized by bluff body flameholders. Emphasis in the program has been on premixed, fuel lean turbulent flames using ethylene, acetylene, propane and propylene fuels with air as the oxidizer. Conclusions of practical interest are (1) combustion noise can be an important contributor to the overall noise problem from turbopropulsion systems if the system extracts high shaft power, (2) it is not important to the nosie problem from afterburning turbopropulsion systems, (3) if the noise output of a particular combustor type is known in one installation, valid predictions may be made for the noise output of the same type of combustor in a different installation and (4) combustion noise may be a contributor to the afterburner instability problem. (Author)
Audible and Ultrasonic Acoustic Emissions from Composite Solid Propellants( Book )

3 editions published between 1975 and 1977 in English and held by 3 WorldCat member libraries worldwide

Audible and ultrasonic acoustic waves are generated during deflagration of composite solid propellants. The audible waves can be sensed by microphones while special high frequency pressure transducers are required to measure the ultrasonic signals. These acoustic emissions have a potential use both as diagnostics of the combustion and as a means for the study of fundamental burning processes. To date a family of composite HTPB-AP propellants have been tested. Results which show the effects of pressure level, atmosphere in which burned, AP particle size, aluminum addition, and aluminum coating are presented and discussed. (Author)
Investigation of the Flame-Acoustic Wave Interaction during Axial Solid Rocket Instabilities( Book )

3 editions published between 1985 and 1991 in English and held by 3 WorldCat member libraries worldwide

The primary objective of this study is the determination of the fundamental mechanisms responsible for the driving of axial instabilities by solid propellant flames. During the report period, the behavior of a premixed flame stabilized on the side wall of a duct in the presence of an axial acoustic field was investigated both theoretically and experimentally. The developed model solutions show that driving occurs due to the combustion process heat addition while outside the reaction zone the waves are damped by viscous processes. This damping increases as the thickness of the acoustic boundary layer increases. Experimental facilities for studying oscillating duct flow sin the presence and absence of flames were developed. Cold flow studies verified the presence of an excess velocity region within the acoustic boundary layer (i.e., the Richardson Effect) and the dependence of the boundary layer thickness upon the frequency and wall injection velocity. Reactive flow studies showed that the behavior of the flame depends upon its location relative to the standing acoustic wave. When the flame was positioned next to a velocity antinode, unexpected instabilities appeared on its surface eventually resulting in severe flame distortion. Also, the measured C-C and C-H radiation signals were periodic and they oscillated with the same frequency as the acoustic wave. Keywords: Flame-Acoustic interactions; and Flame driving
Two approaches to the three-dimensional jet-in-cross-wind problem : a vortex lattice model and a numerical solution of the Navier-Stokes equations by Joe Floyd Thompson( Book )

2 editions published in 1971 in English and held by 3 WorldCat member libraries worldwide

A three-dimensional numerical solution of the time-dependent, incompressible Navier-Stokes equations based on an integro-differential formulation of these equations is developed. With this formulation it is possible to obtain the complete solution in the entire flow field while restricting the actual computational field to the region of significant vorticity magnitude of each time. This allows a considerable reduction in the computer storage required, since only the field points having significant vorticity at any time need be stored at that time, and calculations are actually performed only at those points at that time. The validity of the numerical solution is established by comparison of the results with the exact solution for the time-dependent, one-dimensional flow over a suddenly accelerated infinite flat plate moving parallel to itself at constant velocity, and by comparison of surface pressure and drag coefficients with experimental results and with the results of other numerical solutions for the two-dimensional flow about a circular cylinder. The numerical solution is applied to the flow field of an infinite jet in a cross-flow and to the flow field of a jet issuing perpendicularly from an infinite plane wall into a cross-flow parallel to the wall. (Author)
Noise Suppression in Jet Inlets by Ben T Zinn( Book )

3 editions published between 1978 and 1980 in English and held by 3 WorldCat member libraries worldwide

This report summarizes the work performed during the second year of an AFOSR sponsored research program that was primarily concerned with the development of an analytical technique for determining the radiated sound field from axisymmetric jet engine inlet configurations. The analytical technique employed is based upon an integral representation of the external (radiation) solutions of the Helmholtz equation which describe the sound fields external to a given body under either no flow or constant velocity flow situations. The integral representation developed during the course of this research program is different from earlier works in the sense that it not only yields the correct (unique) solution for all radiation problems at all frequencies, but that the resulting integral equations contain no strong (i.e., nonintegrable) singularities and therefore can be solved by straight forward numerical techniques
Rocket Research at Georgia Tech( Book )

3 editions published between 1979 and 1981 in English and held by 3 WorldCat member libraries worldwide

Progress is reported on four distinct projects which are administered as a group. The individual projects are identified as tasks and reported on separately. A summary for each task follows: Task I. Work concerned improvement and application of the impedance tube method for measurement of the presure-coupled combustion response of solid propellants and measurement of the bulk damping in the product flow. Improvements included increaed sites and amplitude range of pressure measurements; increased capacity of the data acquisition system; and a modified, more rapid data reduction program. Admittances and bulk loss coefficients of nonaluminized and aluminized propellants were measured over a range of frequencies. Task II. Studies were continued on external burning using an axisymmetric model at Mach 3. Tests with actual combustion of radially and axially injected hydrogen are then reported. Outstanding performance values with significant base drag reduction is shown for injection and burning directly in the near-wake (base burning). Task III. Investigations continued of the accumulation processes of aluminum on the propellant burning surface that lead to formation of agglomerate droplets, the size of which dominates aluminum combustion. Task IV. Experimental and analytical studies were continued on the subject of turbulence-induced pressure fluctuations in a rocket-like cavity. A new theory was constructed for the generation of pressure disturbances by the turbulence. Undeniable separation has been achieved between propagational and local pressure fluctuations, and the agreement between theory and experiment are adequate
Combustion Mechanisms of Solid Propellants by E. W Price( Book )

3 editions published between 1980 and 1993 in English and held by 2 WorldCat member libraries worldwide

Investigation of mechanisms of combustion and combustion zone microstructure continued, using ammonium perchlorate-hydro-carbon binder sandwiches and the quench-burning method to obtain high resolution measurements. Binder-thickness deflagration limits were also determined, and work started on measurement of burning rate vs binder thickness. On the basis of results to date, a modified picture of the combustion zone is proposed that differs sharply from the classical model, particularly in those regions of the sandwich surface that are close enough to the AP-binder interface to correspond to processes in solid propellant combustion. (Author)
Integrated Reconfigurable Intelligent Systems (IRIS) for Complex Naval Systems( Book )

3 editions published between 2009 and 2011 in English and held by 2 WorldCat member libraries worldwide

The report details the research work has been done by the Aerospace Systems Design Laboratory (ASDL) in developing and applying the Integrated Reconfigurable Intelligent Systems (IRIS) concept for the period of February 22 to June 30, 2009. The main objective of the work for this period is to further develop and refine the integrated modeling and simulation environment in order to investigate the behavior of complex naval systems for improving the ship design and operations. Five individual tasks were conducted to fulfill this objective. Models revised based on the notional YP were integrated and tested; a control architecture with inference engine was proposed and evaluated based on defined scenarios; comparison of plain NN models and NN models with the block-structure was performed for evaluating accuracy of the surrogate models; a suitable framework and a database engine has been selected to facilitate the information management for developing the HMI of the simulation environment; a robust and a resilient approaches were proposed to conduct design space exploration in order to obtain an ultimate design with increased survivability and mission effectiveness. The rest of the report will explain the accomplishments for each task in details
Sublaminate Damage Mechanisms in Composite Structures( Book )

2 editions published between 1986 and 1987 in English and held by 2 WorldCat member libraries worldwide

This final report summarizes the objectives and accomplishments of research on sublaminate damage mechanisms in composite structures. It may be separated into three elements. The first is interlaminar fracture analysis methodology development. Existing methods for predicting strain energy release rate components have been assessed, and two new alternative approaches have been developed and illustrated. The second is the creation of a phenomenologically based criterion for damage tolerance analysis of composite structures. An equivalent damage parameter and a relevant compliance measure are determined from experiments. This methodology has been validated by seven independent experiments. Keywords: Delamination, Damage tolerance, Damage in composites, Composite materials
Flame Driving of Longitudinal Instabilities in Liquid Fueled Dump Combustors( Book )

2 editions published between 1987 and 1988 in English and held by 2 WorldCat member libraries worldwide

This reports describes the results of experimental and theoretical investigations of the mechanisms by which the core flow combustion process in coaxial, single inlet, dump type ramjet engines drives longitudinal combustion instabilities. To this end, the behavior of V-shaped flames, similar to those often occurring in ramjet combustors, stabilized in longitudinal acoustic fields has been studied. The presence of burning vortical structures is observed in the flame region. These structures appear at frequencies close to the first natural acoustic frequency of the combustor and are believed to be connected with a shear layer type of instability of the flame. Experiments conducted show that the unsteady combustion in these structures is capable of driving the acoustics at the fundamental acoustic mode frequency. With increase in fuel air ratio, a spontaneous instability involving the fundamental mode is observed and explained in terms of increased driving associated with the higher, unsteady heat release rates. Keywords: Coaxial dump type ramjet, Flame driving, Combustion, Acoustics longitudinal instability, Vortex shedding, Shear layer instability. (JES)
A Method of Preliminary Design Analysis for Normal Impact of Earth Penetrators by L. W Rehfield( Book )

1 edition published in 1977 in English and held by 2 WorldCat member libraries worldwide

A simplified method of analysis for use in preliminary design of earth penetrators has been developed. The objectives have been simplicity, rapid turnaround and low cost, in addition to sufficient accuracy for adequate prediction of primary physical processes and associated variables. Based upon a stress wave transmission approach, the method applies to axisymmetric response of projectiles of revolution due to normal impact events in its current state of development. Results are presented for strain and acceleration time histories on a penetrator that has been impact tested. Analysis predictions and available experimental data are in excellent agreement, which indicates that the method is effective as well as efficient. (Author)
Potential Flow Studies of Lift-Fan Inflow Interference Phenomena( Book )

1 edition published in 1973 in English and held by 2 WorldCat member libraries worldwide

The report presents results of a study of the lift-fan inlet problem and includes a comprehensive survey of the existing experimental data and analytical methods, an analysis of the potential flow, and a boundary layer analysis for lift-fan inlets. Numerical solutions are presented for potential flows associated with inlet ducts set in an infinite plane with and without a centerbody simulating the hub of the fan. The effects of the cross flow to mean inlet velocity ratio, of the inlet and hub lip radii to duct width ratio, of the inclination of the duct axis to the plane, and of the position of the hub relative to the plane on the flow in and near the inlet ducts are discussed utilizing a two dimensional potential flow analysis. (Modified author abstract)
Behavior of aluminum in solid propellant combustion by Edward Warren Price( Book )

2 editions published between 1976 and 1977 in English and held by 2 WorldCat member libraries worldwide

The usefulness of powdered aluminum as a propellant ingredient is compromised by the details of its behavior in the combustion zone, its combustion in the motor volume, and by the nature of the product oxide droplets. This project was aimed at clarification of the mechanisms governing concentration, sintering and agglomeration of aluminum on the propellant burning surface, subsequent combustion of agglomerated aluminum, and resulting size distribution of the A1203 product droplets. The approach was to study the response of individual propellant ingredients, and combinations, to controlled heating in laboratory experiments such as hot stage microscope and hot plate apparatus
Combustion Instability in Solid Propellant Rockets( Book )

2 editions published between 1987 and 1989 in English and held by 1 WorldCat member library worldwide

This project concerns assembly, synthesis and comprehensive presentation of information on combustion instability in solid rockets, in the form of a reference book. The format is chosen to make the book suitable for a wide audience of readers including propulsion program managers, motor designers, propellant chemists, test engineers, and combustion specialists. The diversity of audience is accommodated by opening with general introductory chapters for nonspecialist, with progression into more applied issues, such as experimental methods and remedial measures. All chapters open with Introductions that give a relatively non-technical statement of the problem and content, and end with a qualitative summary of what was done in the chapter. An extensive bibliography is included, and supplemented by a more complete, computer-based bibliography with search-retrieval capability
LES of Sooting Flames( )

2 editions published in 2006 in English and held by 0 WorldCat member libraries worldwide

Prediction of soot formation in turbulent flames is a major challenge due to the chemical complexity and the barely understood coupling between soot formation and the other flow transient processes. The current objective is to develop a unified, general methodology for large-eddy simulation (LES) of soot formation and transport in turbulent flames
Controlling mechanisms of pulsating incineration processes by Benjamin T Zinn( )

3 editions published between 1994 and 1996 in English and held by 0 WorldCat member libraries worldwide

The goal of this study is to investigate the fundamental processes that control the performance of acoustically excited incineration systems. Cold flow tests performed under the first year of this program have demonstrated that natural acoustic mode oscillations, in the absence of net flow into or out of the volume, can be used to promote rapid mixing. Increased acoustic pressure amplitudes in the chamber were shown to increase the mixing rates. The dependence of the mixing rate on the mode of acoustic excitation was shown to be highly complex. Acoustic streaming also appears to have a significant influence upon flow and mixing patterns in the simulated incinerator. The effect of acoustic oscillations upon waste incineration was investigated by studying the effect of acoustic oscillations upon dry ice sublimation. This study showed that the presence of pulsations enhanced the sublimation process, which strongly suggests that they would also enhance the process of burning solid wastes. Preparations are underway to investigate the effects of acoustics on the combustion of waste surrogates
Numerical Solution of Three-Dimensional Unsteady Viscous Flows( )

3 editions published between 1991 and 1992 in English and held by 0 WorldCat member libraries worldwide

The long term objective of the present effort is the development of solution techniques for direct numerical simulation of unsteady 3-D incompressible turbulent flows., The kinetic aspects of this problem are governed by a set of parabolic partial differential equations, which may be efficiently integrated by a variety of time marching schemes. The kinematic aspects of this flow such as the relationship between velocity and vorticity, and the relationship between velocity and pressure are governed by elliptic partial differential equations, which can be solved at any instance in time, only by iterative techniques. Direct and/or large eddy simulation of turbulent flows over submarine configurations, turbomachinery, pumps, ducts and other configurations of interest to the U.S. Navy require efficient solution methods for solving the governing equations. The near term objective of the present research is to investigate and develop efficient time marching schemes for integrating the governing equations, and to evaluate the stability and accuracy of the schemes developed by studying a class of 2-D and 3-D unsteady external flows for which good quality experimental and analytical results are available
Technologies for Future Precision Strike Missile Systems( )

3 editions published in 2000 in English and held by 0 WorldCat member libraries worldwide

This report documents the results of NATO Research and Technology Organization (RTO) lecture series number 221, entitled "Technologies for Future Precision Strike Missile Systems." The lecture series was conducted under the RTO Consultant and Exchange (C & E) Program as a two-day educational event, first held March 23-24, 2000 in Atlanta Georgia, at the Georgia Institute of Technology. Following the lectures at Georgia Tech, the lectures were held April 3-4 in Turin, Italy and April 6-7 in Ankara, Turkey. The primary purpose of the lecture series was the disseminating of state-of-the-art scientific and technical knowledge among a wide audience. The lecture series director and three other speakers provided lectures. Emerging technologies for precision strike missile systems that were addressed in the lecture series included
Combustion mechanisms of solids by Edward W Price( )

3 editions published between 1986 and 1992 in English and held by 0 WorldCat member libraries worldwide

A brief summary of ongoing research is presented, including sandwich burning studies with new ingredients, and computational modeling of combustion. Propellant, Combustion, Rocket
 
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English (51)