Suscripción a Biblioteca: Guest
International Journal of Energetic Materials and Chemical Propulsion

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

Indexed in

AEROTHERMOCHEMICAL MODEL FOR THE INTERIOR BALLISTICS OF SOLID PROPELLANT ROCKET MOTORS

Volumen 5, Edición 1-6, 2002, pp. 633-645
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v5.i1-6.660
Get accessGet access

SINOPSIS

A one-dimensional model is formulated to simulate the interior ballistics of a solid propellent rocket motor, considering the mass, momentum and energy conservation equations, applied to a control volume. The model describes the transient ignition process, flame spreading and complete grain burning. The suitable selection of the numerical method allows an efficient solution, resulting in a very low computational cost that permits the use of a personal computer.
Three steps are considered for modeling the ignition transient: induction, flame spreading and combustion chamber filling. The igniter is modeled by an assumed mass flow rate function, with time as the independent variable. For flame spreading calculation, the conservation equations are combined with a heat transfer model, which considers convection from the igniter gases and conduction through the propellant grain. In this way, the grain surface temperature evolution is calculated using a one-dimensional solution to the transient heat conduction equation. Flame spreading is evaluated using a critical temperature of the grain surface: each element of grain surface is assumed to start burning when its calculated temperature reaches the critical value.
An outstanding feature of this model is the changing boundary conditions downstream of the nozzle. Initially, at the start of the ignition process, the zero-flow boundary conditions are set, simulating the nozzle plug. Later, when the plug expulsion pressure is achieved, the boundary conditions change to subsonic outflow. Finally, when the critical pressure is reached in the combustion chamber, boundary conditions turn into supersonic flow. Instability associated with the initial low Mach number flow is solved using an artificial diffusion term. Also included is the blowing effect of the gases generated on the propellant surface on the friction coefficient, and burning rate correlation considering erosive burning.

Portal Digitalde Biblioteca Digital eLibros Revistas Referencias y Libros de Ponencias Colecciones Precios y Políticas de Suscripcione Begell House Contáctenos Language English 中文 Русский Português German French Spain