The burning of periodic sandwich propellants

Hegab, A.; Jackson, T. L.; Buckmaster, J.; Stewart, D. Scott

doi:10.2514/6.2000-3459

Cited by 13 publications

(13 citation statements)

References 18 publications

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“…Recently the complex coupling between the solid-phase and gas-phase process becomes the most factor as a natural step. In particularly, the complexity that arises from the consideration of the unsteady non-planar regression surface, as in [14,15,16].…”

Section: Primary Diffusion Flamesmentioning

confidence: 99%

“…In the study, the propellant surface is not flat and its shape changes with time. Therefore, the following mapping function is used; η = y -f(x,t) (12) and the the front of equation (10) reduces to the simple Hamilton-Jacobi equation; Further information about the non-planar moving of the gas/solid interfaces using the Level Set strategy is mentioned in details in [14,15].…”

Section: 3) Solid-phase and Solid/gas Interface Equationsmentioning

confidence: 99%

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Effect of Ammonium Perchlorate Grain Size on Combustion of a Selected Composite Solid Propellant

Hegab

Balabel

2007

International Conference on Aerospace Sciences and Aviation Tec

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The heterogeneous propellants consisting of Ammonium Perchlorate (AP) particles imbedded in a Hydroxyl Terminated Polybutadience (HTPB) are widely used in solid rocket industries. In this study, the effect of AP particles diameter and the random distribution with the HTPB on the burning of such propellant is presented. A mathematical model which describes the unsteady burning of a heterogeneous propellant by simultaneously solving the combustion fields in the gas phase and the thermal field in the solid phase with appropriate jump condition across the gas/solid interface is developed. The gas-phase kinetics is represented by a two-step reaction mechanism for the primary premixed flame and the primary diffusion flame between the decomposition products of the HTPB and the oxidizer AP. The propagation of the unsteady non-planer regression surface is described, using the Essentially-Non-Oscillatory (ENO) scheme with the aid of the level set strategy. The results show that the large AP particle diameter has a marked effect on the combustion surface deformation and on the burning rate as well. Therefore, modeling of the condensed phase process is mostly conducted on AP. Moreover, the effect of various parameters on the surface propagation speed, flame structure, and the burning surface geometry is obtained.

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Section: Primary Diffusion Flamesmentioning

confidence: 99%

Section: 3) Solid-phase and Solid/gas Interface Equationsmentioning

confidence: 99%

Effect of Ammonium Perchlorate Grain Size on Combustion of a Selected Composite Solid Propellant

Hegab

Balabel

2007

International Conference on Aerospace Sciences and Aviation Tec

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“…In order to have a stable rocket system with desirable performance, individual study for the combustion model that incorporates the burning of microscale propellant and the nonreactive model that accounts the complex fluid flow inside the chamber and the nozzles must be examined first. Some recent studies that consider the burning of microscale solid rocket propellant [1][2][3][4][5][6] concluded that the injection conditions of the cold models in [7][8][9][10][11][12][13][14] are found to be different than that considered with the reactive models [1][2][3][4][5][6]. As a result, the current study is conducted to examine the unsteady flow field inside the solid rocket motor chamber and the complex generated wave and vorticity patterns and their impact on the burning of real solid propellant surfaces.…”

Section: Introductionmentioning

confidence: 99%

Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Hegab

Sait

Hussain

2015

Mathematical Problems in Engineering

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An advanced and intensive computational solution development is integrated with an asymptotic technique, to examine the impact of the combustion surface morphology on the generated rotational flow field in a solid rocket chamber with wide ranges of forcing frequencies. The simulated rectangular chamber is closed at one end and is open at the aft end. The upper and lower walls are permeable to allow steady and unsteady injected air to generate internal flow mimicking the flow field of the combustion gases in real rocket chamber. The frequencies of the unsteady injected flow are chosen to be very close or away from the resonance frequencies of the adapted chamber. The current study accounts for a wide range of wave numbers that reflect the complexity of real burning processes. Detailed derivation for Navier-Stokes equations at the four boundaries of the chamber is introduced in the current study. Qualitative comparison is performed with recent experimental work carried out on a two-inch hybrid rocket motor using a mixture of polyethylene and aluminum powder. The higher the percentage of aluminum powder in the mixture, the more the corrugations of the combustion surface. This trend is almost similar to the computational and analytical results of a simulated solid rocket chamber.

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“…The complex unsteady heat transfer and propellant-surface regression through oxidizer/binder sandwiches, and two-dimensional and three-dimensional random packs of propellant particles have also been modeled using 2-and 3-step global reaction mechanisms to describe the gas-phase heat release. The results of [10][11][12][13][14][15][16] will be discussed below.…”

Section: Previous Modeling Summarymentioning

confidence: 99%

“…Buckmaster, Jackson and co-workers have developed a two-and three-dimensional methodology to describe the geometric effects within solid propellants [10][11][12][13][14][15][16]. The complex unsteady heat transfer and propellant-surface regression through oxidizer/binder sandwiches, and two-dimensional and three-dimensional random packs of propellant particles have also been modeled using 2-and 3-step global reaction mechanisms to describe the gas-phase heat release.…”

Section: Previous Modeling Summarymentioning

confidence: 99%

Recent progress in modeling solid propellant combustion

Beckstead

2006

Combust Explos Shock Waves

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Tremendous progress has been achieved in the last ten years with respect to modeling the combustion of solid propellants. The vastly increased performance of computing capabilities has allowed utilization of calculation approaches that were previously only conceptual. The paper will discuss three areas of emphasis: first, numerical modeling of premixed flames using detailed kinetic mechanisms; second, development of packing models to calculate a geometrical distribution of particles simulating a heterogeneous solid propellant; and finally, calculation of diffusion flame effects that are critical in the combustion of AP/hydrocarbon solid propellants.The capability of modeling premixed combustion using detailed kinetic mechanisms has been evolving and successfully applied to solid propellant ingredients based on a one-dimensional approach. Much of the early work was performed at Novosibirsk. The approach allows calculating the burning rate as a function of pressure but also the temperature sensitivity and spatial distributions of temperature and species concentrations. Generalized mechanisms have been developed and applied to many ingredients such as HMX, GAP, RDX, NG, AP, etc. The gas-phase kinetic mechanisms seem to represent the chemistry of these monopropellants and pseudo-propellants consistently well. The burning rates of these monopropellants vary by almost an order of magnitude but are essentially independent of the flame temperature. Various model calculations agree reasonably well with available experimental data.Recent work in the USA has been aimed at describing the geometrical packing of a solid propellant. These models represent significant progress toward such a description. Combining the packing model with a realistic flame model is still a significant challenge. Preliminary results are encouraging, but obviously further work is needed. Also, fundamental calculation of two-dimensional diffusion flames, incorporating realistic kinetics has progressed significantly. Recent results show encouraging promise toward simulating the minute detail involved in determining the burning rates of AP containing propellants.Key words: modeling, combustion, solid propellant, chemical kinetics. Abbreviations

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The burning of periodic sandwich propellants

Cited by 13 publications

References 18 publications

Effect of Ammonium Perchlorate Grain Size on Combustion of a Selected Composite Solid Propellant

Effect of Ammonium Perchlorate Grain Size on Combustion of a Selected Composite Solid Propellant

Impact of the Surface Morphology on the Combustion of Simulated Solid Rocket Motor

Recent progress in modeling solid propellant combustion

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