Combustion characteristics of a heterogeneous layered system

A review of theoretical research of the combustion of laminate propellants is given. The purpose and description of the simplification of heterogeneous propellants through the use of constituent layers is detailed. This second of a two-part review describes: 1) the development of knowledge of the deflagration of laminates through analytical and computational descriptions of many different aspects of the overall problem; 2) the attempts to validate these theoretical descriptions by comparing their results with relevant experimental findings. While there is a wealth of two-dimensional experimental data available for validating theoretical models and an abundance of models developed, relatively little comparison has been done. As of yet, no model has made a convincing case for validation through sufficiently extensive comparisons to experimental data.

Section: Theoretical and Computational Studiesmentioning

confidence: 83%

Section: Theoretical and Computational Studiesmentioning

confidence: 99%

Laminate Propellant Combustion (Review) 2. Theoretical Investigations

Fitzgerald

Brewster

2006

“…The global kinetics of these processes is described in a simplified manner as a law of linear pyrolysis with an exponential dependence on temperature and a power dependence on pressure. 4. The thermal effect of coolant gasification is endothermal or weakly exothermal and appears owing to coolant decomposition or sublimation.…”

Section: Model Of Combustion Of a Composition With A Coolantmentioning

confidence: 98%

“…Modeling of combustion of the system under study is based on the papers [4][5][6][7][8] and includes the following postulates.…”

Section: Model Of Combustion Of a Composition With A Coolantmentioning

confidence: 99%

Mechanism and laws of combustion of composite solid propellants with a coolant

Strunin

Федорычев

Gunin

et al. 2007

Self Cite

The model of combustion of a composition consisting of a quasi-homogeneous composite propellant (matrix) and coolant particles is considered. The model is based on the leading role of exothermal decomposition of the matrix and on the cooling effect of the second component by virtue of transverse heat transfer between the components in the condensed and gas phases. Formulas for combustion characteristics (temperature, burning rate, its sensitivity to pressure, and initial temperature) are derived and analyzed. The calculated dependences of these characteristics on pressure, particle size, concentration, and thermal effects of decomposition of the components show that transitional regimes with a stronger dependence of the burning rate on pressure than that of the initial propellant are reached in a certain range of parameters. An algorithm is proposed, and a parametric identification of the model on the basis of experimental data is performed.

“…Previously, we modeled this system using a single-zone combustion model for an oxidizer (ammonium perchlorate) and a fuel which is oxidized from the surface or is oxidized and gasified in the gas zone [3][4][5][6]. Two types of combustion were considered, with parameters averaged within each of the layers (one-dimensional approximation) and with parameters distributed over the burning surface (two-dimensional problem).…”

Section: Formulation Of the Problemmentioning

confidence: 99%

Two-zone model for combustion of a composite solid propellant with a coolant

Strunin

Федорычев²,

Gunin³

et al. 2010

Self Cite

A mathematical model for combustion of a propellant with a coolant taking into account the two-zone structure of the combustion front due to condensed-and gas-phase reactions was developed and examined. Formulas for the burning rate, reaction-zone temperature, and burning-rate sensitivity to internal and external parameters of the system were derived in analytical form. The burning rate was examined numerically as a function of pressure, the characteristic size of the system, component content, and thermodynamic and kinetic parameters. Recommendations are given on methods of obtaining particular ballistic properties by varying the initial parameters of the system.