Metallized Gelled Propellants Combustion Experiments in a Pulse Detonation Engine

Palaszewski, Bryan; Jurns, John M.; Breisacher, Kevin J.; Kearns, Kimberly A.

doi:10.2514/6.2004-4191

Cited by 15 publications

(7 citation statements)

References 14 publications

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“…This force field model is detailed in Eq. (7). The MD simulations are used for two purposes: (1) determination of the optimized values for the intermolecular parameters of the COMPASS force field model (last term in Eq.…”

Section: Molecular Dynamicsmentioning

confidence: 99%

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Characterizing high-energy-density propellants for space propulsion applications

et al. 2009

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A technique for computationally determining the thermophysical properties of high-energy-density matter (HEDM) propellants is presented. HEDM compounds are of interest in the liquid rocket engine industry due to their high density and high energy content relative to existing industry-standard propellants. In order to accurately model rocket engine performance, cost and weight in a conceptual design environment, several thermodynamic and physical properties are required over a range of temperatures and pressures. The approach presented here combines quantum mechanical and molecular dynamic (MD) calculations and group additivity methods. A method for improving the force field model coefficients used in the MD is included. This approach is used to determine thermophysical properties for two HEDM compounds of interest: quadricyclane and 2-azido-N,N-dimethylethanamine (DMAZ). The modified force field approach provides results that more accurately match experimental data than the unmodified approach. Launch vehicle and Lunar lander case studies are presented to quantify the system level impact of employing quadricyclane and DMAZ rather than industry standard propellants. In both cases, the use of HEDM propellants provides reductions in vehicle mass compared to industry standard propellants. The results demonstrate that HEDM propellants can be an attractive technology for future launch vehicle and Lunar lander applications.

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Section: Molecular Dynamicsmentioning

confidence: 99%

“…The synthesis and development of HEDM propellants has been investigated by the US Air Force Research Laboratory [1,2], the US Army Research Lab [3,4], the NASA Marshall Space Flight Center [5] and the NASA Glenn Research Center [6,7].…”

Section: Introductionmentioning

confidence: 99%

Characterizing high-energy-density propellants for space propulsion applications

et al. 2009

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“…The brief discussion regarding droplet breakup regime and droplet breakup time is pertinent to the present work, which considers two-phase fluids, consisting of a liquid with a dispersion of metal nanoparticles. The use of metal oxide nanoparticles to increase the energy content of a liquid fuel has been investigated by several researchers [15][16][17], with application to internal combustion [18], gas turbine [19], and pulse detonation engines [20]. Accordingly, the primary motivation for the present work is to study the aerobreakup of two-phase liquid droplets using experiments and simulations.…”

Section: Introductionmentioning

confidence: 99%

Single and two-phase fluid droplet breakup in impulsively generated high-speed flow

Leung¹,

Gurunadhan²,

Menon³

2022

Preprint

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Aerobreakup of fluid droplets under the influence of impulsively generated high-speed gas flow using an open-ended shock tube is studied using experiments and numerical simulations. Breakup of mm-sized droplets at high Weber number was analyzed for water and two-phase nanofluids consisting of dispersions of Al2O3 and TiO2 nanoparticles in water with high loading of 20 and 40 weight% respectively. Droplet breakup is visualized using high-speed imaging in the experimental setup, where an open ended shock tube generates impulsive high-speed flow impinging on a droplet held stationary using an acoustic levitator. Axisymmetric simulations using the Volume of Fluid technique are conducted to capture the gas dynamics of the flowfield and droplet deformation at the initial stages. Fluid droplets are subject to a transient flow field generated by the open ended shock tube, characterized by a propagating incident shock wave, a recirculating vortex ring, and standing shock cells. Droplet breakup for all fluids proceeds through an initial flattening of the droplet followed by generation of a liquid sheet at the periphery in the presence of a curved, detached shock front at the leading edge. The breakup appears to follow a sheet stripping process whereby stretched ligaments undergo secondary atomization through viscous shear. Mist generated in the wake of the droplet appears to expand laterally due to the unconstrained expansion of the high-speed gas jet. The breakup morphology of droplets for all fluids appears consistent with previous observations using conventional shock tubes. Lateral deformation of the coherent droplet mass is observed to be higher for nanofluids as compared to water. This is attributed to higher viscosity and Ohnesorge number of

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“…HEDM propellant research programs by the U.S. Air Force [1,2], U.S. Army [3,4], and NASA [5,6,7] have developed several promising new potential rocket Although a great deal of research has been performed on HEDM propellants, knowledge about the thermophysical properties of these propellants over the range of temperature and pressure experienced in liquid rocket engines is limited. As a result, one has three main options available for designing rocket engines that utilize these propellants.…”

Section: Introductionmentioning

confidence: 99%

Characterizing High-Energy-Density Propellants for Space Propulsion Applications

Kokan

Olds

Seitzman

et al. 2008

Journal of Thermophysics and Heat Transfer

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Metallized Gelled Propellants Combustion Experiments in a Pulse Detonation Engine

Cited by 15 publications

References 14 publications

Characterizing high-energy-density propellants for space propulsion applications

Characterizing high-energy-density propellants for space propulsion applications

Single and two-phase fluid droplet breakup in impulsively generated high-speed flow

Characterizing High-Energy-Density Propellants for Space Propulsion Applications

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