Behavior of Aluminum in Solid Propellant Combustion.

Price, Ed; Sigman, R. K.; Sambamurthi, J.K.; Park, C J

doi:10.21236/ada035569

Cited by 8 publications

(10 citation statements)

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“…Combustion of aluminum fuel is of vital interest [14][15][16][17][18][19][20]. The aluminum particles are initially located among the coarse fractions of the oxidizer particles (in areas called pockets) and also, if D AP /D Al 1, in narrow channels of interpockets connections (in areas called bridges).…”

Section: Burning Mechanism By Visual Inspection Of Aluminized Composimentioning

confidence: 99%

“…According to Price [13][14][15][16], cracking of the protective hard oxide shell actually involves a variety of additional factors affecting, in a multifaceted way, the already intricate heating-ignition-combustion events. When the temperature is below the Al 2 O 3 melting point, liquid aluminum leaking through a single or multiple ruptures of the oxide shell is subjected to oxidation, thus, promoting resealing of the fractured shell.…”

Section: Burning Mechanism By Visual Inspection Of Aluminized Composimentioning

confidence: 99%

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Burning of Nano-Aluminized Composite Rocket Propellants

Luca

Galfetti

Severini

et al. 2005

Combust Explos Shock Waves

213

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Several aluminum nanopowders were examined and compared with the final goal to evaluate their application in solid rocket propulsion. A detailed investigation of pre-burning properties by the Brunauer-Emmet-Teller method, electron microscopy, X-ray diffraction, and X-ray photoelectron spectroscopy was carried out. Ballistic properties and the combustion mechanism of several aluminized propellant formulations were investigated. In particular, aggregation and agglomeration of metal particles at and near the burning surface were analyzed by high-speed high-resolution color digital video recordings. All tested nano-powders are of Russian production; their physical characterization was carried out at the Istituto Donegani (Novara, Italy); ballistic studies were performed at the Solid Propulsion Laboratory (Milano, Italy) using laboratory and, for comparison, industrial composite propellants based on ammonium perchlorate as an oxidizer. Results obtained under a fair variety of operating conditions typical of rocket propulsion indicate, for increasing nano-Al mass fraction or decreasing nano-Al size, larger steady burning rates with essentially the same pressure sensitivity. While aggregation and agglomeration phenomena still occur, their significance may be reduced by using nano-Al instead of micro-Al.

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Section: Burning Mechanism By Visual Inspection Of Aluminized Composimentioning

confidence: 99%

Section: Burning Mechanism By Visual Inspection Of Aluminized Composimentioning

confidence: 99%

Burning of Nano-Aluminized Composite Rocket Propellants

Luca

Galfetti

Severini

et al. 2005

Combust Explos Shock Waves

213

View full text Add to dashboard Cite

show abstract

“…However, as a result of the long ignition delays of aluminum particles in heating to the aluminum ignition temperature (~2300 K, the oxide melting temperature), aluminum particles can depart the burning surface and combust relatively far away from the burning surface. If high enough temperatures are reached near the burning surface, oxide shells can crack as a result of stress induced from aluminum core phase changes allowing the aluminum to leak out [4]. These molten particles can then sinter to other molten metal particles, resulting in larger agglomerates of condensed-phase aluminum and aluminum oxide particles [5,6].…”

Section: Motivationmentioning

confidence: 99%

Organically-Capped, Nanoscale Alkali Metal Hydride and Aluminum Particles as Solid Propellant Additives

Lawrence

Laktas²,

Place³

et al. 2019

Journal of Propulsion and Power

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“…Metal fuel additives are commonly used in explosives, propellants, and pyrotechnics [1][2][3]. It is often desired to control their burn rate, depending on the application or specific operational scenario [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Combustion of Magnesium‐Sulfur Composite Particles Ignited by Different Stimuli

Monk

Schoenitz

Dreizin

2018

Propellants Explo Pyrotec

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Composite Mg · S powders were prepared by mechanical milling. Magnesium powders coated with sulfur were prepared by soft milling using glass beads as milling media. Three-dimensional composite powders, in which magnesium and sulfur were mixed on the nanoscale were prepared by milling using steel balls as milling media. Both composite powders were explored in two ignition experiments. In one case, monolayers of the prepared powders were exposed to electrostatic discharge (ESD). In the other case, powder particles were fed through a focused CO 2 laser beam. In both experiments, emission traces produced by burning particles were captured using a filtered photomultiplier tube; the data were processed to recover respective combustion times. Combustion products were col-lected and examined using electron microscopy for the ESD-ignition experiments. It was found that the burn times of the sulfur coated magnesium powders were shorter than those of three-dimensional composites in both experiments. No effect of ignition method on burn times was observed for the sulfur-coated powders. For three-dimensional composite powder, burn times of ESD-ignited particles were shorter than those for particles ignited by passing through the CO 2 laser beam. Analysis of the captured combustion products suggests that magnesium and sulfur are readily separated upon heating for the coated powders, but not for the three-dimensional composites. For the latter case, the reaction is dominated by MgS formation, while for the former case, it is primarily magnesium oxidation in air.

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Behavior of Aluminum in Solid Propellant Combustion.

Cited by 8 publications

References 0 publications

Burning of Nano-Aluminized Composite Rocket Propellants

Burning of Nano-Aluminized Composite Rocket Propellants

Organically-Capped, Nanoscale Alkali Metal Hydride and Aluminum Particles as Solid Propellant Additives

Combustion of Magnesium‐Sulfur Composite Particles Ignited by Different Stimuli

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