Modeling of aluminum oxide particle radiation in a solid propellant motor exhaust

Plastinin, Yu. A.; Anfimov, N. A.; Baula, G.; Karabadzhak, G. F.; Khmelinin, B.; Родионов, А. В.

doi:10.2514/6.1996-1879

Cited by 11 publications

(9 citation statements)

References 5 publications

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“…It is a nonequilibrium process, and the recession of the crystallization front is described by the equation [3] r s dr s =dt a T m T s 1:…”

Section: A Kinetics Process Of Liquid-to-gamma-phase Transitionmentioning

confidence: 99%

“…When exposed to the cold environment, the cooling alumina particles will crystallize and pass through different phase states, and so the radiative properties of the alumina particle's various phase states should be considered accurately during crystallization. Plastinin et al [3] studied the spectral radiance of rapidly cooling (3 10 3 K=s) melted alumina particles and indicated that the time dependence of spectral radiative properties is obvious during their crystallization processes and that the effects of equilibrium and nonequilibrium crystallization processes are important in the simulation of the solid propellant motor plume's radiative properties. Rodionov et al [4] simulated alumina particles' phase transitions and undercooling phenomena in the plume flowfields.…”

mentioning

confidence: 99%

“…Introduction P ARTICLE radiation is an important issue for heat transfer or spectral radiation signal transmission in high-temperature a combustion system such as a boiler furnace, a rocket engine combustion chamber, and an exhaust plume [1][2][3][4]. A solid aluminized rocket motor produces large amounts of alumina particles, which are the main cause of the plume's radiative properties.…”

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confidence: 99%

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Modeling for the Transient Radiative Properties of Alumina Particles with Phase Transition

Dong

et al. 2008

Journal of Thermophysics and Heat Transfer

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Nomenclature F x = volume fraction of the x component in the whole particle f = portion of the phase during the transition from the phase to the phase I = particle's spectral radiance k = imaginary part of the complex refractive index (absorption coefficient) m = complex refractive index of the mixture M x = portion of the x phase in the whole particle m x = complex refractive index of the x component n = real part of the complex refractive index (refractive index) Q abs; = absorption factor of the particle r = radius of the particle r L = equivalent radius of the liquid fraction of the particle r s = equivalent radius of the solid fraction of the particle r s = relative crystallization-front radius T m = equilibrium melting temperature T s = crystallization-front temperature V x = volume of the x component t = time step " = spectral emissivity of the particle " x = dielectric constant of the x component " = dielectric constant of the mixture " d = dielectric constant of the host medium Subscripts L = liquid phase = alpha phase = gamma phase

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“…It is a nonequilibrium process, and the recession of the crystallization front is described by the equation [3] r s dr s =dt a T m T s 1:…”

Section: A Kinetics Process Of Liquid-to-gamma-phase Transitionmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Modeling for the Transient Radiative Properties of Alumina Particles with Phase Transition

Dong

et al. 2008

Journal of Thermophysics and Heat Transfer

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“…While thermal radiative properties of aluminium oxide particles/droplets formed by combustion of aluminium have been studied fairly extensively [1][2][3][4][5][6][7][8][9][10][11][12][13] thermal emission properties of burning aluminium droplets themselves have not [14,15]. Yet thermal radiation from burning aluminium can be a significant mode of heat transfer in various devices and settings, particularly aluminised solid rocket motors (SRMs).…”

Section: Introductionmentioning

confidence: 99%

Analysis of thermal radiation from burning aluminium in solid propellants

Harrison

Brewster

2009

Combustion Theory and Modelling

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Thermal emission from burning aluminium droplets in solid propellants has been analysed using radiative transfer theory and infrared intensity measurements from emission images of burning droplets at 1-5 atm. Below 5 atm, infrared emission is dominated by the burning droplet, not the detached flame zone around the droplet. Each droplet consists of a molten metal portion and a molten oxide (cap) portion. Emission from the metal portion of the droplet surface is spatially uniform and corresponds with opaque surface theory. Emission from the oxide cap portion of the droplet surface is spatially non-uniform and corresponds with volumetric emission from a non-opaque surface. The oxide cap was approximated as a truncated section of a sphere. The burning droplet temperature was found to be approximately 300 K below the metal boiling point. Account was also taken for non-isothermal particulate emission by the sub-micron oxide smoke cloud formed in the detached flame zone around the droplet. The analysis was able to represent infrared emitted intensity reasonably well for various oxide cap thicknesses and orientation angles. Extending the analysis to include all wavelengths suggested that smoke envelope emission becomes more important at shorter (e.g., visible) wavelengths. A simple, linear relation for the incremental increase in total (spectrally and directionally integrated) droplet emissivity owing to smoke envelope emission was obtained at 1 atm: ε = 0.001D(µm).

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“…Bird [9] proved the consistency of the DSMC method and the Boltzmann equation by mathematical derivation method. In view of the physical essence of DSMC, various numerical models are introduced to simulate complex physical and chemical processes [10], especially for the thermochemical non-equilibrium [11], radiation [12], and gas-solid interaction [13] and other complex problems.…”

Section: Introductionmentioning

confidence: 99%

Study on Chemical Reactions of Ions and Neutral Particles on the Wall with DSMC Method

Su¹,

Li²,

Fan³

2018

Proceedings of the 2018 3rd International Conference on Automation, Mechanical Control and Computational Engineering (AMCCE 201

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Abstract. Plasma plumes exist widely in the electric propulsion systems. Neutral particles, ions, and metal particles are included in the flow field. Complex collisions occur between the particles. Particles will collide with the wall surface when they move towards the wall, then some particles will reflect back, the others will react on the wall with a certain probability. Chemical reactions on the wall have a significant effect on the distribution of the particles and lead to the change of density in the flow field. The chemical reaction models on the wall are studied based on the direct simulation of Monte Carlo method (DSMC). Five types of particles including molecular hydrogen H 2 , atomic hydrogen H, atomic Titanium Ti, ion H 2 + , and ion H + are studied in the flow field, there are chemical reactions for these particles with a certain probability on the wall. The numerical simulation results show that the number density of molecular hydrogen H 2 increases obviously, the number density of atomic hydrogen H increases slightly, and the number density of ion H + decreases significantly after adding the chemical reaction models on the wall, indicating that the chemical reactions on the wall have a significant influence on the distribution of the particles in the flow field. The study in this paper provides basic data for further research on plasma plumes by the numerical simulation.

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Modeling of aluminum oxide particle radiation in a solid propellant motor exhaust

Cited by 11 publications

References 5 publications

Modeling for the Transient Radiative Properties of Alumina Particles with Phase Transition

Modeling for the Transient Radiative Properties of Alumina Particles with Phase Transition

Analysis of thermal radiation from burning aluminium in solid propellants

Study on Chemical Reactions of Ions and Neutral Particles on the Wall with DSMC Method

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