Flow Inside a Solid Rocket Motor with Relation to Nozzle Inlet Ablation

Shimada, Toru; Sekiguchi, Masumi; Sekino, Nobuhiro

doi:10.2514/1.22952

Cited by 27 publications

(13 citation statements)

References 9 publications

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“…• Simulation of vortex-shedding [38] and thrust oscillation [39] with the view point of the adaptive control [40], of the effect of burning aluminum droplets [41], of the nozzle cavity effect [42], of the wall and the inhibitor effect [43,44], and of the large solid rocket boosters [45][46][47][48][49]. • Simulation of the internal flow with respect to the nozzle ablation [50][51][52] and to the roll-torque generation [53]. • Simulation of combustion stability [54].…”

Section: Reliability and Simulationmentioning

confidence: 99%

Solid propulsion for space applications: An updated roadmap

Guery¹,

Chang

Shimada

et al. 2010

Acta Astronautica

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Section: Reliability and Simulationmentioning

confidence: 99%

Solid propulsion for space applications: An updated roadmap

Guery¹,

Chang

Shimada

et al. 2010

Acta Astronautica

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“…The particle impingement erosion observed in nozzle liners and chamber insulation materials is affected by the presence of aluminum oxide and unburned aluminum in the exhaust gases. Asymmetric mass flux distributions caused by propellant grain slots often increase the impingement erosion in circumferential areas in line with the grain slots [6].…”

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confidence: 99%

Effects of Propellant Gases on Thermal Response of Solid Rocket Nozzle Liners

Hwang

Yim

2008

Journal of Propulsion and Power

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The propellant formulations, the gas properties in motor chamber, and the aluminum oxide particle sizes for two kinds of solid propellants with approximately 20% aluminum powder have been investigated. The scanning electron microscope photographs of aluminum oxide particles taken from a nozzle entrance show that the aluminized polycaprolactone polyol propellant with 47% volumetric fraction ammonium perchlorate/hexanitro hexaazaisowurtzitane and the bimodal oxidizers, 200=5 m, can offer greater possibility for increasing aluminum agglomeration than the aluminized hydroxy-terminated polybutadiene propellant with 64% volumetric fraction ammonium perchlorate and the trimodal oxidizers, 400=200=6 m. The aluminized polycaprolactone polyol propellant with energetic plasticizers results in locally greater mechanical erosion in four circumferential sections of the nozzle entrance in line with grain slots, due to the impingement of large particles. However, the hydroxyterminated polybutadiene propellant results in greater thermochemical ablation at the blast tube, the throat insert, and the exit cone of rocket nozzle, due to 2.3 times more water and carbon dioxide oxidizing species in exhaust gases than the polycaprolactone polyol propellant. Nomenclature A = cross-sectional flow area c p = specific heat of gases at constant pressure d p = diameter of aluminum oxide particle E 0 = activation energy of a chemical reaction h = convective heat transfer coefficient K 0 = preexponential factor of a chemical reaction k = mass fraction of the solid residue of material M 0 = molecular weight of gas mixture M c = molecular weight of carbon P w = pressure at nozzle wall R = ideal gas constant T w = temperature at nozzle wall CO 2 = mole fraction of CO 2 H 2 O = mole fraction of H 2 O 0 = initial density Subscripts t = conditions at nozzle throat w = wall conditions

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“…Comprehensive theoretical/ numerical models have been developed previously by the authors to predict [5][6][7] and mitigate [8] the chemical erosion of a nozzle surface. Several numerical studies [9][10][11][12] were carried out using an Eulerian-Lagrangian approach to account for the effect of alumina particles on the motor flow dynamics. There was, however, either no treatment [9,10] or limited qualitative treatment [11,12] of the mechanical erosion of a rocket nozzle.…”

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confidence: 99%