Relative Dispersion of Catalytic Nanoparticle Additives and AP Particles in Composite Solid Propellant and the Effect on Burning Rate

Kreitz, Kevin R.; Petersen, Eric L.; Reid, David L.; Seal, Sudipta

doi:10.2514/6.2011-418

Cited by 14 publications

(5 citation statements)

References 8 publications

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“…This more oxidizer-rich formulation increases the propellant ame temperature from 2300 K to 2800 K, which produces a faster burning rate and a higher degree of pressure sensitivity. 44 Based on our previous work, 45 the bimodal size distribution of AP particles is expected to produce combustion rates that are more sensitive to the degree of TiO 2 nanoparticle agglomeration. A variety of these propellants were prepared using HTPB binders containing in situ, solution-mixed, and powder/melt-mixed TiO 2 nanoparticles.…”

Section: Composite Solid Propellant Performancementioning

confidence: 99%

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In situ synthesis of polyurethane–TiO2 nanocomposite and performance in solid propellants

et al. 2014

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Section: Composite Solid Propellant Performancementioning

confidence: 99%

“…f c is a function of the relative dispersion of the catalyst particles and the oxidizer particles. 45 A qualitative expression for this relationship is shown in eqn (4).…”

Section: Composite Solid Propellant Performancementioning

confidence: 99%

In situ synthesis of polyurethane–TiO2 nanocomposite and performance in solid propellants

et al. 2014

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“…Metal oxides can be synthesized using various techniques by changing their morphology to tailor their catalytic behavior. [3][4][5][6][7] Most studies used a CO 2 laser with a wavelength of 10.6 μm; the present study used the same CO 2 laser wavelength at a power ranging from 30 to 100 W. AP and HTPB propellants have been shown to have high absorption and low reflection at this 10.6-μm wavelength. Fine AP particles and carbon black can be added to the propellant to aid in ignition by increasing the opacity of the propellant, allowing more energy to be absorbed.…”

Section: Introductionmentioning

confidence: 98%

“…3 Nelson-Jackson Professor, Department of Mechanical Engineering, Senior Member AIAA. 4 Research Assistant Professor, Advanced Materials Processing and Analysis Center (AMPAC). 5 Professor and Director, Advanced Materials Processing and Analysis Center (AMPAC).…”

Section: Introductionmentioning

confidence: 99%

Ignition Delay Times of Composite Solid Propellants Using Novel Nano-Additive Catalysts

Demko¹,

Dillier²,

Petersen³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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Ignition delay time measurements on solid energetic materials lead to better fundamental understanding of the ignition process and provide benchmark data for improving models of the ignition process. Validation for such models is typically done by collecting ignition data over a wide range of propellant formulations. This study focused on the development of a setup to obtain ignition delay times of AP/HTPB-based composite solid propellants with and without aluminum and with and without various metal-oxide nanoparticle catalysts. A CO 2 laser with a wavelength of 10.6 μm was utilized to achieve a quantifiable and reliable ignition event over a power range of 30 to 100 W. AP and HTPB propellants have been shown to have high absorption and low reflection at this 10.6-μm wavelength. Resulting from this study was the development of a method to measure the ignition delay time for ammonium perchlorate composite propellants (APCP) at elevated pressures between 3.5 and 15.5 MPa. A comparison of the laser power flux as it relates to the change in ignition delay time was found to match available literature values at similar conditions. Additional studies to examine the effects of in-situ titania nanoparticles on the ignition delay times demonstrated that the nano-additives only appeared to alter the ignition behavior of the aluminized APCP.When iron-oxide was added, the ignition delay time was reduced at lower pressures. Additives which aid in the low-temperature decomposition of AP are believed to impact the ignition delay times the most. Nomenclature a = burning rate constant (also called temperature coefficient) n = pressure coefficient in burning rate relation P = pressure r = burning rate T = temperature σ p = propellant temperature sensitivity

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“…Recent propellant studies have involved the effect of nano-additives to tailor burning rate characteristics [4][5][6][7][8][9][10]. With new formulations and novel nano-particle manufacturing techniques specific to propellants, examining the aging characteristics of the resulting composite is of interest.…”

Section: Introductionmentioning

confidence: 99%

Aging Effects of Composite AP/HTPB Propellants Containing Nano-Sized Additives

Sammet¹,

Demko²,

Dillier³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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The aging behavior of a composite propellant is a key indicator in the service life of a practical rocket motor. Advancements in the development of nano-particle additives and their burning rate enhancing characteristics give rise to examining the long-term impacts on the service life of the motor. Recent research at Texas A&M has focused on tailoring ballistic characteristics through the addition of nano-additives specifically synthesized for composite propellants. This paper focuses on an AP/HTPB propellant with a dry-powder nano-titania additive to influence ballistic characteristics and fluorescing Lumidots to assess morphological changes associated with accelerated aging. Sample sets were aged at 85 o C in ambient humidity conditions for six and twelve days, simulating four and eight years of aging, respectively. Data were correlated to a set of naturally aged samples. Acceleratedaged monomodal AP formulations with 80% solids loading and nano-additive demonstrated an approximate 7% decrease in burning rate, with accompanying morophological changes. Accelerated-aged bimodal AP forumlations with 85% solids loading and nano-additive demonstrated an approximate 12% increase in burning rates, with accompanying morphological changes. Nomenclature a = burning rate constant (also called temperature coefficient) n = pressure coefficient in burning rate relation P = pressure r = burning rate

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Relative Dispersion of Catalytic Nanoparticle Additives and AP Particles in Composite Solid Propellant and the Effect on Burning Rate

Cited by 14 publications

References 8 publications

In situ synthesis of polyurethane–TiO2 nanocomposite and performance in solid propellants

In situ synthesis of polyurethane–TiO2 nanocomposite and performance in solid propellants

Ignition Delay Times of Composite Solid Propellants Using Novel Nano-Additive Catalysts

Aging Effects of Composite AP/HTPB Propellants Containing Nano-Sized Additives

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