Regression rates of metalized hybrid fuel systems.

Smoot, L.D.; Price, C. F.

doi:10.2514/3.3566

Cited by 72 publications

(17 citation statements)

References 2 publications

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“…This effort entailed the development of an analytical expression for the regression rate as a function of several kinetic parameters and length-scales. Miller [20] developed a model that incorporated both the fuel diffusion rate and the chemical reaction rates, which he used to successfully correlate data taken by Smoot and Price [21][22][23]. Kosdon and Williams [24] later noted that Miller's analysis was only applicable to systems with low pressure and moderate oxidizer fluxes and derived a new expression that incorporated a flame zone of finite thickness.…”

Section: Kinetics-limited Modelsmentioning

confidence: 99%

“…Another group of researchers focused more on heterogeneous surface reactions as the source of kinetics dependence. Smoot and Price [21][22][23] performed numerous tests using a slab burner and found that, above a threshold value of G, the regression rate became nearly independent of G and instead varied with P and the oxidizer composition. These researchers defined a low mass flux regime where the normal G 0.8 dependence held, an intermediate mass flux regime where both P and G played a role, and a third regime at very high mass fluxes where the regression rate varied with pressure, as in the case of a solid rocket propellant; namely,ṙ ∝ P n .…”

Section: Kinetics-limited Modelsmentioning

confidence: 99%

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Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Marquardt

Majdalani

2019

Aerospace

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In this article, we undertake a concise review of several milestone developments in classical regression rate models of hybrid rocket motors. After a brief description of the physical processes entailed in hybrid rocket combustion, Marxman's diffusion-limited theory is re-constructed and discussed. Considerations beyond the scope of basic convection-driven models, which address disparate forms of the blowing correction, variable fluid properties, and pressure and radiation effects, are also given. Finally, a selection of kinetically-limited models is presented, with the aim of comparing the characteristics of several competing theories that become applicable under particular circumstances.

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Section: Kinetics-limited Modelsmentioning

confidence: 99%

Section: Kinetics-limited Modelsmentioning

confidence: 99%

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Marquardt

Majdalani

2019

Aerospace

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“…Besides the traditional strategy of the addition of highly energetic metallic particles such as micron‐sized or nanoscale aluminum, and boron , it is found that the addition of H‐enriched materials that can introduce more hydrogen into the combustion system will increase the combustion efficiency of a fuel, promote lower pollutant emissions, and enhance the heat of combustion and specific impulse, etc. . Therefore, H‐enriched materials such as metal hydrides, complex hydrides (borohydrides, alanates), and borane compounds have been proposed to be potential candidates of solid propellants (Table ) .…”

Section: Introductionmentioning

confidence: 99%

Ignition and Combustion Behaviors of High Energetic Polyhedral Boron Cluster

Pan

Jiang

et al. 2019

Propellants Explo Pyrotec

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Compounds containing [B10H10]2− cluster are promising candidates that can be used as high energetic fuels and burning rate modifiers for propellants. The ignition and combustion behaviors of [N(C2H5)4]2B10H10 were investigated using a laser ignition system in air. Results show that [N(C2H5)4]2B10H10 (∼2.0 mm) is ignited with a delay of around 350 ms and threshold ignition energy of 0.7 J at laser ignition power density of 1.14×107 W/m2. Furthermore, the combustion of [N(C2H5)4]2B10H10 in air is found to undergo three stages of decomposition, incomplete combustion of the volatile pyrolytic products, and ejection and combustion of the molten dehydrogenated framework, giving massive smoke and a characteristic pyrotechnic flame.

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“…A definitive pressure dependence of fuel regression ra te was noted in [15] and [16] for a lithium hydride based fuel grain w ith a FLO X oxidizer, and various non-m etallized polym er fuels operating w ith a FLO X oxidizer. T he pressure depen dencies were observed at m ass flux > 70 k g /m 2s and low pressures, < 1 5 0 psia, and were a ttrib u te d to a heterogeneous ra te lim iting kinetic reaction a t th e oxidizer/fuel…”

Section: Influence O F Pressure On Regression Ratementioning

confidence: 98%

“….21 taken from[35].Note th a t the axes ranges are not labeled, as th e existence and extent of each regime would vary w ith fuel form ulation. Portions of this figure have been experim entally explored for various fuels (for exam ple in References[15] and[16]) b u t a com plete picture of the regression ra te functionality has not been produced over large pressure 83 and m ass flux ranges for any fuel to date.…”

mentioning

confidence: 99%

Experimental and numerical study of a hydrogen peroxide / hydroxyl terminated polybutadiene hybrid rocket

Farbar¹

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E x p e r im e n ta l an d N u m e r ic a l S tu d y o f a H y d ro g en P e r o x id e / H y d ro x y l T erm in a ted P o ly b u ta d ie n e H y b rid R o c k e t by E rin Far b a r, B . E n g . A thesis subm itted to th e Faculty of G rad u ate Studies and Research in p a rtial fulfillment of th e requirem ents for the degree of M a s te r o f A p p lie d S c ie n c e O ttaw a-C arleton In stitu te for M echanical and Aerospace Engineering D epartm ent of M echanical and Aerospace Engineering C a r le to n U n iv e r s ity O ttaw a, O ntario, C anada Novem ber 25, 2005Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. Library and A rch iv es C a n a d a P u b lish ed H eritage Branch W ellington StreetOttawa ON K1A 0N4 Canada B ib lioth eq u e et A rch iv es C a n a d a D irection du P atrim oine d e I'editionBien que ces formulaires aient inclus dans la pagination, il n'y aura aucun contenu manquant. i * i Canada Reproduced with permission of the copyright owner. Further reproduction prohibited without permission.t tu rb u len t quantity xviii Reproduced with permission of the copyright owner. Further reproduction prohibited without permission.

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Regression rates of metalized hybrid fuel systems.

Cited by 72 publications

References 2 publications

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Ignition and Combustion Behaviors of High Energetic Polyhedral Boron Cluster

Experimental and numerical study of a hydrogen peroxide / hydroxyl terminated polybutadiene hybrid rocket

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