Download or read book Multidimensional Modeling of Composite Solid Propellant Combustion written by Graham D. Kosiba and published by . This book was released on 2017 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Multidimensional Modeling of Solid Propellant Burning Rates and Aluminum Agglomeration and One dimensional Modeling of RDX GAP and AP HTPB written by Matthew Wilder Tanner and published by . This book was released on 2008 with total page 244 pages. Available in PDF, EPUB and Kindle. Book excerpt: This document details original numerical studies performed by the author pertaining to solid propellant combustion. Detailed kinetic mechanisms have been utilized to model the combustion of the pseudo-propellants RDX/GAP and AP/HTPB. A particle packing model and a diffusion flame model have been utilized to develop a burning rate and an aluminum agglomeration model.

Download or read book Multidimensional Effects in Composite Propellant Combustion written by Sung-Taick Lee and published by . This book was released on 1991 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Multidimensional Effects in Composite Propellant Combustion written by Sung-Taick Lee (|d) and published by . This book was released on 1999 with total page 165 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Development of a Computerized Analysis for Solid Propellant Combustion Instability with Turbulence written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A multi-dimensional numerical model has been developed for the unsteady state oscillatory combustion of solid propellants subject to acoustic pressure disturbances. Including the gas phase unsteady effects, the assumption of uniform pressure across the flame zone, which has been conventionally used, is relaxed so that a higher frequency response in the long flame of a double-base propellant can be calculated. The formulation is based on a premixed, laminar flame with a one-step overall chemical reaction and the Arrhenius law of decomposition with no condensed phase reaction. In a given geometry, the Galerkin finite element solution shows the strong resonance and damping effect at the lower frequencies, similar to the result of Denison and Baum. Extended studies deal with the higher frequency region where the pressure varies in the flame thickness. The nonlinear system behavior is investigated by carrying out the second order expansion in wave amplitude when the acoustic pressure oscillations are finite in amplitude. Offset in the burning rate shows a negative sign in the whole frequency region considered, and it verifies the experimental results of Price. Finally, the velocity coupling in the two-dimensional model is discussed. Chung, T. J. and Park, O. Y. Unspecified Center NAG8-627...

Download or read book Two dimensional Solid Propellant Combustion Modeling by Finite Element Calculations written by O. Y. Park and published by . This book was released on 1987 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Combustion Response Modeling for Composite Solid Propellants written by Norman S. Cohen and published by . This book was released on 1978 with total page 137 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to develop a computerized mathematical model of the combustion response function of composite solid propellants, with particular attention to the contributions of the solid phase heterogeneity. A one-dimensional model was developed which treats the solid phase as alternating layers of AP and binder, with an exothermic melt layer at the surface. Solution of the Fourier heat equation in the solid provides temperature and heat flux distributions with space and time. The problem is solved by equating the heat flux at the surface to that produced by a suitable model of the gas phase. An approximation of the BDP flame model is utilized to represent the gas phase. By the use of several reasonable assumptions, it is found that a significant portion of the problem can be solved in closed form. A method is presented by which the model can be applied to tetramodal particle size distributions. A computerized steady-state version of the model was completed, which served to validate the various approximations and lay a foundation for the combustion response modeling. It is concluded that some other mechanism associated with the propellant heterogeneity must be incorporated into the theory to account for observed behavior.

Download or read book An Intrinsic Heterogeneous Model of Composite Solid Propellant Combustion written by Bryan Michael Rasmussen and published by . This book was released on 1999 with total page 240 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Multidimensional Combustion Flow Modeling of Aluminized Solid Propellants written by Eric Gerard Bradley and published by . This book was released on 1990 with total page 280 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Simplified Combustion Modeling of Composite Propellants written by and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Non linear Heterogeneous Model of Composite Solid Propellant Combustion written by B. Rasmussen and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Combustion Modeling of Composite Solid Propellants written by John Paul Renie and published by . This book was released on 1982 with total page 255 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Synergistic Effects and Deflagration Analysis in Composite Solid Propellant Combustion written by and published by . This book was released on 1975 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Using four common catalysts the existence and magnitude of synergistic effects upon burn rate are studied with HTPB-AP composite solid propellants. The effect under study is one whereby at a fixed total catalyst loading the mixture of two catalysts would be more effective in burn rate augmentation than a single catalyst. At 2000 psia all possible combinations of catalysts showed synergistic effects but the effects are weak and within the reproducibility range of the experiments. Ferric oxide and iron blue showed synergistic effects only at 300 and 2000 psia over the pressure range 300-2000 psia. Analysis of the effect of binder-oxidizer reactions upon the surface shape of a two-dimensional sandwich has shown that (a) the faster are these reactions the more deeply will the sandwich obtain a V-shape and b) these reactions are generally fast enough to indeed affect the surface shape.

Download or read book Nonsteady Burning and Combustion Stability of Solid Propellants written by Martin Summerfield and published by AIAA. This book was released on 1992 with total page 922 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Combustion Response Calculations for Composite Solid Propellants written by J. P. Renie and published by . This book was released on 1981 with total page 203 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this report, the theoretical, steady state combustion model, the Petite Ensemble Model (PEM), is described in detail. The PEM is based upon a combination of a unique statistical treatment of the burning propellant surface and a comprehensive multiple flame type, physio-chemical combustion model. Due to this statistical treatment, the PEM can account for both oxidizer particle size and oxidizer particle size distribution effects on burning rate behavior; an unique feature of this model. The effects on propellant burning rate behavior due to the inclusion of aluminum particles have been taken into account within this version of the PEM, as have any possible effects caused by the presence of a crossflow velocity above the propellant surface (erosive burning). The PEM is capable of modeling the burning behavior of AP-based/hydrocarbon binder, composite solid propellants. Propellant additives such as aluminum oxide, zirconium carbide and graphite, as well as aluminum, can also be incorporated in the propellant formulations modeled by the PEM. This report presents the results obtained by applying a small perturbation analysis to the equations representing the steady state PEM (including aluminum and erosive burning effects). Performing such an analysis yields nonsteady state models of both the pressure coupled response and the velocity pressure coupled response of composite solid propellants. Other historical pressure coupled response models such as the Dension and Baum mode, the Cohen model, and the Zeldovich/Novozhilov model are also briefly described. Finally, a second velocity coupled response model based on the Zeldovich/Novozhilov methodology coupled to the erosive burning PEM is presented. (Author).

Download or read book Multi Dimensional Combustion Instability Analysis of Solid Propellant Rocket Motors written by T. J. Chung and published by . This book was released on 1985 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: Analytical models are developed for the multi-dimensional combustion instability analysis of solid propellant rocket motors. This research was motivated by the need for improvement of the current practice in combusiton instability analysis. For example, the burning rates and response functions are affected by the extremely complex flowfield. The flow is three-dimensional or at least two-dimensional in axisymmetric geometries; vortex motions and turbulent flows must be adequately calculated; the coupling mechanism of acoustic and hydrodynamic wave oscillations and particle damping should be clarified. These flowfield phenomena, after all, are originated from the flame zone activities - oscillatory behavior of all field variables such as temperature, velocity, pressure, density of the gas, and fuel fractions. The response functions, which serve as boundary conditions for the flowfield can be calculated from the first and second order perturbation eigenvalue analyses of the flame zone governing equations. The effect of velocity coupling appears, naturally, in the second order (nonlinear) solutions. All calculations are carried out using the finite element method. Some of the findings are summarized.

Download or read book Solid Propellant Combustion Modeling written by George D. Sammons and published by . This book was released on 1973 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report covers the first 15 months of a continuing study on construction of a comprehensive mathematical model of composite solid propellant combustion, with emphasis on work during the past 12 months since reporting on the early efforts at the meeting last year. The liquid layer believed to exist on burning ammonium perchlorate has been treated in a manner similar to that described previously. Depth of penetration of a thermal wave is calculated and this value is multiplied by the surface area of oxidizer on the burning propellant surface. The surface is calculated in the computer program for use in other equations. Total volume of the liquid layer derived in this manner is then used to calculate the thermal contribution to surface temperature. (Modified author abstract).