WorldCat Identities

Flandro, G. A. (Gary A.) 1934-

Works: 18 works in 33 publications in 1 language and 600 library holdings
Genres: Textbooks  Academic theses 
Roles: Author
Classifications: TL574.F5, 629.1323
Publication Timeline
Most widely held works by G. A Flandro
Basic aerodynamics : incompressible flow by G. A Flandro( Book )

13 editions published between 2011 and 2012 in English and held by 96 WorldCat member libraries worldwide

"In the rapidly advancing field of flight aerodynamics, it is important for students to completely master the fundamentals. This text, written by renowned experts, clearly presents the basic concepts of underlying aerodynamic prediction methodology. These concepts are closely linked to physical principles so that they may be more readily retained and their limits of applicability are fully appreciated. The ultimate goal is to provide the student with the necessary tools to confidently approach and solve of practical flight vehicle design problems of current and future interest. The text is designed for use in course in aerodynamics at the advanced undergraduate or graduate level. A comprehensive set of exercise problems is included at the end of each chapter"--
Trajectory optimization and guidance law development for national aerospace plane applications : final report, July 1, 1987 to November 30, 1988 by Anthony J Calise( Book )

1 edition published in 1988 in English and held by 69 WorldCat member libraries worldwide

Stability Prediction for Solid Propellant Rocket Motors with High Speed Mean Flow by G. A Flandro( Book )

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

Current stability prediction calculations for solid propellant rocket motors are based upon a simple first-order perturbation solution which assumes an incompressible chamber mean flow. Since combustion instability is frequently observed in motors with large length-to-diameter and low port-to-throat area ratios, there is concern that the standard stability techniques should be extended to apply to cases where high-speed mean flows are present. This report shows how the basic stability analysis can be extended by carrying additional terms in the perturbation expansions. Compressibility affects the calculations in several ways. The acoustic mode shapes predicted in the linear model are distorted and the mean thermodynamic properties may vary significantly from point to point in the chamber. These variations and distortions alter both the predicted growth rates and also the frequencies for the acoustic modes. Detailed calculations are carried out for a cylindrical grain geometry with longitudinal wave motions. Frequency and growth rate corrections grow quadratically with increases in the port length-to-diameter ratio. Frequency shifts of as much as 30 percent of the linear acoustic frequency predictions may be expected in high L/D motors. (Author)
Fluid Mechanics of Spinning Rockets( Book )

1 edition published in 1987 in English and held by 2 WorldCat member libraries worldwide

This report presents the results of a detailed investigation of the influence of time-dependent combustion gas flows on the attitude dynamics of spinning rocket propelled space vehicles. The work was motivated by a need to understand the origins of a potentially serious system performance problem first detected in the PAM-D series of spin stabilized upper stages. Small wobbling (often referred to as nutation or coning) induced during separation of the rocket motor burn. The growth ceased abruptly at motor burnout, and final cone angles as large as 17 deg were reached in some flights. The same phenomenon was encountered in two flights of the PAM-DII, a similar vehicle utilizing a larger motor. Conventional theories of spinning rocket dynamics failed to explain this behavior. Since the telemetry data shows that the severity of the problem depends on spacecraft mass properties and other system parameters, it is crucial that the origins of the instability be understood completely in order that serious mission degradation can be avoided in future orbit raising operations. A costly interim fix, which sidesteps the need to understand the physical origins of the problem, is the use of a strap-on nutation control system as used in the Air Force SGS II missions. This approach is in direct conflict with the philosophy of solid rocket space propulsion, which is based on its inherent simplicity and low cost
Predicted spacecraft attitude behavior by G. A Flandro( Book )

1 edition published in 1987 in English and held by 1 WorldCat member library worldwide

Oscillatory internal flow in solid propellant rocket motors by G. A Flandro( Book )

1 edition published in 1992 in English and held by 1 WorldCat member library worldwide

Acoustic Energy Balance Method( Book )

1 edition published in 1984 in English and held by 1 WorldCat member library worldwide

A useful analytical model for nonlinear rocket instability must adequately represent the following characteristics: (1) steep fronted waves, (2) limit cycle operation, and (3) triggering phenomena. To include all of these important attributes requires retention of terms to third order in the perturbation parameter representing the system amplitude. This leads to an extremely complicated analysis; means must be found to develop useful analytical models that retain some physical clarity. Application of energy methods often results in simplification of the formulation. In this paper the energy method is combined with a simplified representation of the wave structure to produce an approximate model for axial pressure fluctuations in a tubular port which demonstrates all of the nonlinear characteristics of importance. Effects of nonlinear combustion and losses in shock waves are included
Study of dynamic interactions between hypersonic vehicle aerodynamics and propulsion system performance by G. A Flandro( Book )

in English and held by 1 WorldCat member library worldwide

The Study of Crack Criticality in Solid Rocket Motors( Book )

1 edition published in 1971 in English and held by 1 WorldCat member library worldwide

Assuming that burning in cracks and debonds in solid propellant grains will occur, the present paper analyzes the pressure distributions in these flaws during the burning process. A preliminary analysis of fracture propagation is included by which estimates of initial flaw propagation velocity are made. It is shown that varieties of flaws can exist where the pressure loading within the flaw may be sufficient to cause mechanical propagation velocities in excess of the burning rate. (Author)
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
Solar electric low thrust missions to Jupiter with swingby continuation to the outer planets by G. A Flandro( Book )

1 edition published in 1968 in English and held by 1 WorldCat member library worldwide

Flow Induced Nutation Instability in Spinning Solid Propellant Rockets( Book )

1 edition published in 1990 in English and held by 1 WorldCat member library worldwide

The work studies rocket motor internal ballistics on the observed coning instability of spinning, orbit raising propulsion stages. This phenomenon appeared in the PAM-D (STAR 48) vehicles. Unexpected coning appeared near the end of motor burn with final cone angles nearly 15 deg. Earlier vehicles of similar design were not afflicted. While no PAM missions were lost, lighter vehicles using the same propulsion concept and spin stabilization could be jeopardized. The exact cause of the instability needs to be found and corrected at the design stage. A better understanding is needed for attitude control systems to be designed on a rational basis. Capability to estimate nutation amplitudes is needed in system design decisions. These needs are met in the form of rational scaling laws that allow extension of experimental data to motor/ spacecraft configurations. Numerous physical mechanisms have been proposed to explain the PAM-D disturbing torque with most eliminated by failure to comply with telemetry data. Two mechanisms still remain to be more fully evaluated. One is the slag sloshing hypothesis, which links the instability to sloshing of accumulations of aluminum oxide slag within the aft closure of the rocket motor combustion chamber. This mechanism is preferred because it is similar to the familiar liquid stores sloshing nutation source with the driving mechanism linked to the mass center offset caused by the relative motion of the pool of liquid material. However, this interpretation predicts a sensitivity to vehicle acceleration that does not appear in the data. A much more massive vehicle, the SGS-II first stage, also employing the STAR 48 exhibits a torque gain factor that does not reflect acceleration sensitivity
The Influence of Mean Flow on Rocket Motor Combustion Instability. Volume I. Basic Analysis, Mean Flow Application to the T-Burner. Volume II. Effect of Turbulence on Acoustic Waves in a Cavity. Volume III. Vortex Generated Sound in Solid Propellant( Book )

1 edition published in 1972 in English and held by 1 WorldCat member library worldwide

The report consists of two problems related to acoustic combustion instability in solid propellant rockets. In the first problem, coupled acoustic cavities with mass flux across a common boundary are studied. Since the propellant grain in a solid rocket motor may assume various configurations to meet specific performance criteria, physical models considering two or more wave-carrying systems coupled together so that acoustic motion of each is affected by the other are required in the study of acoustic instability in some motor designs. In the second problem, linear analyses employing both one-dimensional and three-dimensional flow models of the T-burner are studied to resolve which is the more appropriate representation of the growth of acoustic models yield an identical expression for the acoustic growth rate of dominant longitudinal modes in the T-burner if properly formulated. (Author)
Nonlinear Interactions between Vortices and Acoustic Waves in a Rocket Combustion Chamber( Book )

1 edition published in 1984 in English and held by 1 WorldCat member library worldwide

In order to carry out useful predictive analyses of solid propellant rocket or ramjet combustion oscillation problems, it is necessary that all loss and gain mechanisms be accounted for. Recent motor experience has demonstrated that flow of oscillatory energy from vortex shedding to the acoustic field of the chamber is one of these mechanisms; in the ramjet problem it is probably the major source of oscillatory behavior. The coupling between the vortex instability which arises in regions of highly sheared flow and the chamber acoustic field represents a problem of great complexity. In this paper, a detailed analysis is described which addresses several basic features of this coupling. Some of the goals of the analysis are: (1) Determine growth rate corrections for use in standard stability assessment codes, (2) Determine the limit cycle processes of the vortical region of flow, and (3) Assess the global limiting behavior of the coupled nonlinear acoustical/vortical flow
Rotating flows in acoustically unstable rocket motors by G. A Flandro( )

1 edition published in 1967 in Undetermined and held by 1 WorldCat member library worldwide

One of the most interesting manifestations of acoustic combustion instability in solid propellant rocket motors is the formation of strong vortices in the combustion chamber. A single vortex filament stretching along the motor axis from the head-end has been observed in several experiments in association with gas oscillations in the frequently occurring traveling tangential mode of instability. These flows are sometimes accompanied by a quite noticeable axial torque on the motor itself, and this effect has given rise to flight performance difficulties in a number of instances. Previous theoretical studies of the vortex generation effect have been inadequate in several respects. The present work is an attempt to place the theory on a more firm base and to clarify the connection between traveling wave motions and the generation of vortices and torques. It is readily shown that traveling waves transport momentum, and in the case of traveling tangential waves in a cylindrical combustion chamber this represents a steady axial component of angular momentum in the gas. This observation gives rise to a simple conceptual model of the vortex generation effect. Thus the presence of a steady mass flux about the axis implies the existence of a layer of vorticity at the chamber walls which may be represented by a vortex sheet composed of axially oriented bound vortex filaments. In the three-dimensional case these vortices are shed either at the end of propellant grain or at the periphery of the nozzle; the other ends of the filaments traverse the fore-end closure to the center and are combined and shed in an intense vortex filament along the symmetry axis of the motor. Due to the production of gas at the chamber wall, tangential forces at the wall are produced by the interaction of this mean flow with the bound vortices. Angular momentum arguments must be used in this conceptual mechanism to estimate the strength of the axial vortex filament, and it is readily shown that the sens
Rotating flows in acoustically unstable rocket motors by G. A Flandro( Book )

1 edition published in 1967 in English and held by 1 WorldCat member library worldwide

Investigations of Novel Energetic Materials to Stabilize Rocket Motors( )

1 edition published in 2002 in English and held by 0 WorldCat member libraries worldwide

This document is the final report of the Caltech Multidisciplinary University Research Initiative (MURI), "Investigations of Novel Energetic Materials to Stabilize Rocket Motors," ONR Contract No. N00014-95-1-1338. With a one-year no-cost extension, the program covered the period 1 October 1995 to 30 September 2001 and involved Principal Investigators at nine Universities. In addition, for three years, funds from another source supported research by seven Russian research groups. Participants in the Caltech MURI provided technical oversight of that work. A second MURI devoted to the same general subject was carried out at the University of Illinois at Urbana- Champaign (UIUC). The two programs were largely complementary. Some of the sections in this report have been co-authored by representatives of both MURIs. Similarly, the final report of the UIUC MURI will contain some duplication of material covered in this document. The Caltech MURI was a multidisciplinary program devoted to research on fundamental problems of the chemistry, combustion and gas dynamics of novel energetic propellants and their unsteady behavior in rocket motors. This program achieved significant progress towards the ultimate overall objective of research in this field, to identify and quantify the influences of propellant composition on the stability of motions in a solid propellant rocket motor. To attain that objective it is essential to support cross-disciplinary effort between propellant chemists and researchers; combustion researchers; and researchers concentrating on the dynamics of solid rocket combustors. This MURI program was the first sustained effort to accomplish the necessary collaborations among faculty and students in universities, with participation by representatives of government laboratories and industry; in the many respects described in this report the program has been highly successful
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Alternative Names
Flandro, G.A.

Flandro, Gary A. 1934-

Gary Flandro American engineer

Gary Flandro Amerikaans ingenieur

Gary Flandro ingegnere aerospaziale statunitense

Gary Flandro ingeniero estadounidense

English (31)