Modeling and numerical simulation of ignition transient of large solid rocket motors PDF Download
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Author: Ferruccio Serraglia
Publisher:
ISBN:
Category :
Languages : it
Pages : 99
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Author: Ferruccio Serraglia
Publisher:
ISBN:
Category :
Languages : it
Pages : 99
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Author: In-Hyun Cho
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: P. Venugopal
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Brian Anthony McDonald
Publisher:
ISBN:
Category : Solid propellant rockets
Languages : en
Pages :
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Book Description
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: Zhen-Guo Wang
Publisher: John Wiley & Sons
ISBN: 1118890043
Category : Technology & Engineering
Languages : en
Pages : 396
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Book Description
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: Gary Daniel Luke
Publisher:
ISBN:
Category : Internal combustion engines
Languages : en
Pages : 422
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Author: P. V. S. Alavilli
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Nicolas Lupoglazoff
Publisher:
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Category :
Languages : en
Pages :
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Author: M. A. Eagar
Publisher:
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Category :
Languages : en
Pages :
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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723025761
Category :
Languages : en
Pages : 176
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Book Description
This report presents the results of experimental and numerical investigations of the flow field in the head-end star grain slots of the Space Shuttle Solid Rocket Motor. This work provided the basis for the development of an improved solid rocket motor ignition transient code which is also described in this report. The correlation between the experimental and numerical results is excellent and provides a firm basis for the development of a fully three-dimensional solid rocket motor ignition transient computer code. Foster, Winfred A., Jr. and Jenkins, Rhonald M. and Ciucci, Alessandro and Johnson, Shelby D. Unspecified Center COMBUSTIBLE FLOW; COMPUTATIONAL FLUID DYNAMICS; COMPUTER PROGRAMS; SOLID PROPELLANT IGNITION; SPACE SHUTTLE BOOSTERS; FLOW DISTRIBUTION; IGNITERS; MATHEMATICAL MODELS; SLOTS; SOLID PROPELLANT ROCKET ENGINES...
