Numerical Simulation S of Model Solid Rocket Motor Flows PDF Download
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Author: P. Venugopal
Publisher:
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Languages : en
Pages :
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Author: P. Venugopal
Publisher:
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Category :
Languages : en
Pages :
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Author: Zhen-Guo Wang
Publisher: John Wiley & Sons
ISBN: 1118890027
Category : Technology & Engineering
Languages : en
Pages : 392
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This book concentrates on modeling and numerical simulations of combustion in liquid rocket engines, covering liquid propellant atomization, evaporation of liquid droplets, turbulent flows, turbulent combustion, heat transfer, and combustion instability. It presents some state of the art models and numerical methodologies in this area. The book can be categorized into two parts. Part 1 describes the modeling for each subtopic of the combustion process in the liquid rocket engines. Part 2 presents detailed numerical methodology and several representative applications in simulations of rocket engine combustion.
Author: Sourabh Apte
Publisher:
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Category :
Languages : en
Pages :
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Author: M. Mettenleiter
Publisher:
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Category :
Languages : en
Pages : 14
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This article describes current developments in the numerical simulation of active control. The objective of this investigation is to devise software tools for the development of active control. The present approach uses a numerical simulation of the system based on the Navier-Stokes equations. It differs from the more standard simulations relying on lower order dynamical models. The main difficulties associated with the present strategy are related to the representation of the actuator in the flow simulation module and with the interfacing of this module with the adaptive control routine. These issues require careful treatment to obtain a suitable commercial model of How control. It is first shown that the actuator may be described by a distribution of sources in the field. The time stepping needed by the flow simulation module and by the control unit differ widely (the ratio between the time steps is of the order of 100 or more). This constitutes a source of perturbation and it may introduce unwanted high frequency components in the flow simulation. It is shown that this problem is alleviated by placing numerical filters at the controller input and output. A set of calculations are carried out to simulate vortex shedding instabilities of a simplified solid propellant rocket. These instabilities are then adaptively controlled. This example serves to illustrate the simulation methodology and provides insights into the operation of the flow controller.
Author: Gao Bo
Publisher:
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Category :
Languages : en
Pages :
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Author: Brian Anthony McDonald
Publisher:
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Category : Solid propellant rockets
Languages : en
Pages :
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The development of an erosive burning model for solid rocket motors using direct numerical simulation Brian A. McDonald 93 Pages Directed by Dr. Suresh Menon. A method for developing an erosive burning model for use in solid propellant design-and-analysis interior ballistics codes is described and evaluated. Using Direct Numerical Simulation, the primary mechanisms controlling erosive burning (turbulent heat transfer, and finite rate reactions) have been studied independently through the development of models using finite rate chemistry, and infinite rate chemistry. Both approaches are calibrated to strand burn rate data by modeling the propellant burning in an environment with no cross-flow, and adjusting thermophysical properties until the predicted regression rate matches test data. Subsequent runs are conducted where the cross-flow is increased from M=0.0 up to M=0.8. The resulting relationship of burn rate increase versus Mach Number is used in an interior ballistics analysis to compute the chamber pressure of an existing solid rocket motor. The resulting predictions are compared to static test data. Both the infinite rate model and the finite rate model show good agreement when compared to test data. The propellant considered is an AP/HTPB with an average AP particle size of 37 microns. The finite rate model shows that as the cross-flow increases, near wall vorticity increases due to the lifting of the boundary caused by the side injection of gases from the burning propellant surface. The point of maximum vorticity corresponds to the outer edge of the APd-binder flame. As the cross-flow increases, the APd-binder flame thickness becomes thinner ; however, the point of highest reaction rate moves only slightly closer to the propellant surface. As such, the net increase of heat transfer to the propellant surface due to finite rate chemistry affects is small. This leads to the conclusion that augmentation of thermal transport properties and the resulting heat transfer increase due to turbulence dominates over combustion chemistry in the erosive burning problem. This conclusion is advantageous in the development of future models that can be calibrated to heat transfer conditions without the necessity for finite rate chemistry. These results are considered applicable for propellants with small, evenly distributed AP particles where the assumption of premixed APd-binder gases is reasonable.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 45
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A summary of research on our studies of acoustic-mean flow interactions in solid rocket motors is presented in this Final Technical Report. Two-dimensional, time-dependent solutions of the compressible Navier-Stokes equations have been obtained in a rectangular duct under conditions of monochromatic acoustic forcing. The existence of a cut-off frequency, the appearance of oblique waves, and the behavior at resonance compare well with previously published analytical predictions. The thickness of the acoustic boundary layer and its response to imposed disturbances are also in good agreement with theory. The code is being modified to include nonpremixed combustion, which will allow studying acoustic interactions with a chemically reactive mean flow. (MM).
Author: Ferruccio Serraglia
Publisher:
ISBN:
Category :
Languages : it
Pages : 99
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Author: T. M. Smith
Publisher:
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Category :
Languages : en
Pages :
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Author: In-Hyun Cho
Publisher:
ISBN:
Category :
Languages : en
Pages :
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