Aging Effects on the Burning Rates of Composite Solid Propellants with Nano-Additives

Thomas, James C.; Sammet, Thomas; Dillier, Catherine A.; Demko, Andrew R.; Rodriguez, Felix A.; Petersen, Eric L.

doi:10.2514/1.b37189

Cited by 23 publications

(1 citation statement)

References 50 publications

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“…The inclusion of metal oxides, such as iron oxide (Fe2O3) and titanium oxide (TiO2), in composite AP/HTPB propellants has been observed to increase the global burning rates [2][3][4][5][6][7][8][9][10][11][12][13][14][15]. It is well documented in the literature that metal oxides enhance the thermal decomposition of AP [16].…”

Section: Metal Oxides In Solid Propellantsmentioning

confidence: 99%

Burning Rate Characterization of Ammonium Perchlorate Pellets Containing Micro- and Nano-Catalytic Additives

Rodriguez

Thomas

Sammet

et al. 2022

Journal of Propulsion and Power

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Ammonium perchlorate (AP) is an extensively used oxidizer in solid composite propellants, and its combustion behavior can be tailored by the presence of catalytic additives such as metal oxides. Nano-sized metal oxide catalysts have been utilized in place of their micro-sized counterparts to tailor burning rates of composite Ammonium Perchlorate (AP)/Hydroxyl-terminate Polybutadiene (HTPB) propellants. The effects of micro-and nano-sized metal oxide catalysts on the combustion of AP were investigated and thoroughly characterized herein.AP pellets were manufactured with micro-and nano-iron oxide (Fe2O3) and micro-and nano-titanium oxide (TiO2) at several mass loadings (0-3% by mass) and were burned from 3.45-34.5 MPa (500-5,000 psi) in a constant-volume strand bomb.Intimate contact between the AP and micro-or nano-catalysts was ensured using a Resonant Acoustic Mixer (RAM). The homogenous mixture of AP and catalyst was pressed into pellets using a Carver hydraulic press. The sides of the pellets were inhibited prior to burning to discourage side-wall burning.The incorporation of 1% µFe2O3 yielded the highest burning rate among all formulations herein within the investigated pressure range. The incorporation of nTiO2 and nFe2O3 yielded burning rates which were independent of mass loading within the range of evaluated conditions (0.25-1%). All micro-formulations investigated increase the burning rate at pressures ranging from roughly 13. 500 psi) and 4.50-8.60 MPa (650-1,250 psi) and for µTiO2 and µFe2O3, respectively; and these viii

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Section: Metal Oxides In Solid Propellantsmentioning

confidence: 99%

Burning Rate Characterization of Ammonium Perchlorate Pellets Containing Micro- and Nano-Catalytic Additives

Rodriguez

Thomas

Sammet

et al. 2022

Journal of Propulsion and Power

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A constitutive model of solid propellants considering aging and confinement pressure

Qin,

Zhang,

Zhang

et al. 2024

Propellants Explo Pyrotec

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Aging during storage and confinement pressure during launch are the two major loading conditions that affect the integrity of solid rocket motors. In comparison to other component materials, solid propellants, as highly filled composites, have a low modulus and fracture toughness and are therefore common sources of failure. The key to improving the integrity of the solid rocket motor is in assessing the health of the solid propellants during storage or launch. To address this issue, we revised the previous model for the progressive damage viscoelasticity of solid propellants to include the effect of chemical aging during storage and the influence of confinement pressure during launch. Specifically, the increase in relaxation time due to aging and the nonequilibrium volume dilatation characteristics under triaxial tension and compression of solid propellants have been considered. To validate the developed model, standard relaxation tests and uniaxial tensile tests on solid propellants without aging were used to calibrate the model parameters. Furthermore, the model was validated by comparison with uniaxial tensile tests under confined pressure after aging and well predicts the aging temperature/time‐dependent mechanical responses of solid propellants. After validation, the developed model was used to study the influence of confinement pressure on microscopic damage evolution and macroscopic volume expansion. Overall, the developed model can be used for the analysis of the integrity of the solid rocket motor after the aging process.

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Graphene oxide–supported Cu/Co nano-catalysts for thermal decomposition of ammonium perchlorate composites

Liang,

Song,

Chen

et al. 2023

Adv Compos Hybrid Mater

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Aging Effects on the Burning Rates of Composite Solid Propellants with Nano-Additives

Cited by 23 publications

References 50 publications

Burning Rate Characterization of Ammonium Perchlorate Pellets Containing Micro- and Nano-Catalytic Additives

Burning Rate Characterization of Ammonium Perchlorate Pellets Containing Micro- and Nano-Catalytic Additives

A constitutive model of solid propellants considering aging and confinement pressure

Graphene oxide–supported Cu/Co nano-catalysts for thermal decomposition of ammonium perchlorate composites

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