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Book The Development of an Erosive Burning Model for Solid Rocket Motors Using Direct Numerical Simulation

Download or read book The Development of an Erosive Burning Model for Solid Rocket Motors Using Direct Numerical Simulation written by Brian Anthony McDonald and published by . This book was released on 2004 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Book Engineering of Solid Rocket Motors

Download or read book Engineering of Solid Rocket Motors written by José A. F. F. Rocco and published by Cambridge Scholars Publishing. This book was released on 2023-05-17 with total page 505 pages. Available in PDF, EPUB and Kindle. Book excerpt: In the last few years, the aerospace industry has grown exponentially for both military and civil applications. This book explores the systems engineering, production processes and performance issues which happen constantly during solid rockets operations and flight. It also discusses state of the art experiments and techniques, as well as many recent developments. The book will appeal to rocket scientists, students and lecturers, senior scientists and professors.

Book Numerical Simulation S of Model Solid Rocket Motor Flows

Download or read book Numerical Simulation S of Model Solid Rocket Motor Flows written by P. Venugopal and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Modeling and numerical simulation of ignition transient of large solid rocket motors

Download or read book Modeling and numerical simulation of ignition transient of large solid rocket motors written by Ferruccio Serraglia and published by . This book was released on 2003 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book Scientific and Technical Aerospace Reports

Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 488 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.

Book Modeling of Crack Initiation and Growth in Solid Rocket Propellants Using Macromechanics and Micromechanics Theories

Download or read book Modeling of Crack Initiation and Growth in Solid Rocket Propellants Using Macromechanics and Micromechanics Theories written by James H. Lee and published by . This book was released on 1996-09-01 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt: Modeling and simulation of crack initiation and propagation in solid rocket propellant materials were conducted using both the macromechanics approach and the micro/macromechanics approach. Due to their composition, the solid rocket propellant can be construed as particle reinforced composites. The macromechanics approach entailed a numerical simulation of a finite element model to predict the crack behavior based on the damage initiation, growth, and local saturation. Its results were then compared to the experimental data. In the simulation, it was assumed that a crack forms when a damage is saturated in a localized zone. The results from the simulation were quite comparable to the experimental results, validating the method of predicting crack initiation, growth, and arrest using the concept of damage growth and saturation. The second approach involved using a simplified micromechanical model and the damage mechanics being applied at the micromechanics level and the finite element analysis being done subsequently at the macromechanics level. In using this approach, the damage modes such as matrix cracking, interface debonding and particle cracking were explainable in an explicit fundamental manner. Several simulations were conducted using this approach including the cases of non- uniform particle distribution. The predicted results compared well with the experimental data.

Book Dissertation Abstracts International

Download or read book Dissertation Abstracts International written by and published by . This book was released on 2005 with total page 780 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Book A Model of Erosive Burning of Composite Propellants

Download or read book A Model of Erosive Burning of Composite Propellants written by Merrill K. King and published by . This book was released on 1977 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Development of solid rocket motor designs which result in high velocity flows of product gases across burning propellant surfaces(notably, nozzleless rocket motors) is leading to increased occurrence of erosive burning. In this paper, a physically realistic picture of the effect of such crossflow on composite propellant combustion, based on the bending of columnar diffusion flames by the crossflow, is presented. This bending results in shifting of the diffusion flame heat release zone toward the surface, with consequent increased heat feedback flux from this flame to the surface and thus increased burning rate. A relatively simple analytical model based on this picture is developed for prediction of propellant burnings rate as a function of pressure and crossflow velocity, given only zero-crossflow burning rate versus pressure data. Model predictions and experimental results are compared, with reasonably good agreement being found. (Author).

Book Erosive Burning of Composite Propellants

Download or read book Erosive Burning of Composite Propellants written by and published by . This book was released on 1976 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: Increasing use of solid rocket motors with low port-to-throat area ratios, including the ultimate case of nozzleless motors, is leading to increased occurrence and severity of burning rate augmentation due to flow of propellant products across burning propellant surfaces (erosive burning). A review of the literature regarding this phenomenon indicates a lack of systematic data defining the effects of propellants formulation variables on the sensitivity of burning rate to crossflow velocity and the absence of a realistic predictive model for composite propellant burning rate-pressure-velocity relationships. In this paper, a physically realistic picture of the effect of crossflow velocity on composite propellant combustion is presented and a relatively simple analytical model based upon this picture is developed for prediction of composite propellant burning rate as a function of pressure and crossflow velocity, given only the burning rate-pressure relationship in the absence of cross-flow. In addition, hardware developed for testing erosive burning effects at cross flow Mach numbers up to 1.0 is described and a planned systematic test matrix is defined. Preliminary test results are included and compared with predictions made using the aforementioned analytical model.

Book Numerical Simulation of Vortex Shedding Phenomenon in 2D Test Case Solid Rocket Motors

Download or read book Numerical Simulation of Vortex Shedding Phenomenon in 2D Test Case Solid Rocket Motors written by Nicholas Lupoglazoff and published by . This book was released on 1992 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: