On the performance of solid propellants containing metal additives

Cheung, H.; Cohen, N.

doi:10.2514/6.1964-116

Cited by 8 publications

(10 citation statements)

References 4 publications

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“…They can contribute to two-phase flow losses (thermal and viscous disequilibrium through the nozzle), which can reduce overall motor performance by as much as 10% [1,23,39]. Additionally, large condensed phase droplets have been shown to cause combustion inefficiencies, energy losses from the combustion products to the rocket motor hardware (i.e., heat loss and droplet impingement), and boundary layer losses; together, these losses can contribute an additional 2-8% overall performance loss [1].…”

Section: Solid Propellant Formulation and Combustion Characteristicsmentioning

confidence: 99%

Removing hydrochloric acid exhaust products from high performance solid rocket propellant using aluminum-lithium alloy

Terry¹,

Sippel

Pfeil³

et al. 2016

Journal of Hazardous Materials

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Hydrochloric acid (HCl) pollution from perchlorate based propellants is well known for both launch site contamination, as well as the possible ozone layer depletion effects. Past efforts in developing environmentally cleaner solid propellants by scavenging the chlorine ion have focused on replacing a portion of the chorine-containing oxidant (i.e., ammonium perchlorate) with an alkali metal nitrate. The alkali metal (e.g., Li or Na) in the nitrate reacts with the chlorine ion to form an alkali metal chloride (i.e., a salt instead of HCl). While this technique can potentially reduce HCl formation, it also results in reduced ideal specific impulse (ISP). Here, we show using thermochemical calculations that using aluminum-lithium (Al-Li) alloy can reduce HCl formation by more than 95% (with lithium contents ≥15 mass%) and increase the ideal ISP by ∼7s compared to neat aluminum (using 80/20 mass% Al-Li alloy). Two solid propellants were formulated using 80/20 Al-Li alloy or neat aluminum as fuel additives. The halide scavenging effect of Al-Li propellants was verified using wet bomb combustion experiments (75.5±4.8% reduction in pH, ∝ [HCl], when compared to neat aluminum). Additionally, no measurable HCl evolution was detected using differential scanning calorimetry coupled with thermogravimetric analysis, mass spectrometry, and Fourier transform infrared absorption.

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Section: Solid Propellant Formulation and Combustion Characteristicsmentioning

confidence: 99%

Removing hydrochloric acid exhaust products from high performance solid rocket propellant using aluminum-lithium alloy

Terry¹,

Sippel

Pfeil³

et al. 2016

Journal of Hazardous Materials

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“…These devices are based on the impact of the particles trailed by a supersonic flow on a collection plate. Microscopy observations would be performed on the particles collided with the collection plate in order to have an insight into the CCPs particle size and structure [8] [9]. The technique was not optimal since it did not take into account the possible T American Institute of Aeronautics and Astronautics effect of shock waves and coalescence in the exhaust plume, these last processes leading to liquid particle shattering and coalescence, respectively.…”

Section: Literature Surveymentioning

confidence: 99%

“…The technique was not optimal since it did not take into account the possible T American Institute of Aeronautics and Astronautics effect of shock waves and coalescence in the exhaust plume, these last processes leading to liquid particle shattering and coalescence, respectively. These studies pointed out that the CCP particle size was slightly affected by the combustion chamber pressure (i.e., low pressure promotes smaller particles [9]), the propellant composition, the expansion ratios, the residence time, and, the initial metal particle diameter. The initial metal particles diameter inside the motor was one order magnitude lower with respect to the CCP size, clearly suggesting that the coalescence process occurred in the nozzle [8].…”

Section: Literature Surveymentioning

confidence: 99%

“…• the supersonic mixing in the straight channel is modeled with a progressive secondary flow addition (uniform differential mass flow rate) with a local recomputation of average properties of the fluid. Since according to Kessel [9], the merging of different boundary layers or stagnant presence of the cooling inert gas inside the mixing straight duct could lead to possible fluid dynamic instabilities, the divergent shape was selected during the design phase and the dilution gas must be injected at high speed. Hence, internal diffuser and nitrogen conditions have been selected accordingly.…”

Section: Fluid Dynamic Analysismentioning

confidence: 99%

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Overview of a Supersonic Probe for Solid Propellant Rocket CCP Collection

Carlotti

Maggi

Bisin

et al. 2018

2018 Joint Propulsion Conference

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“…27 On the basis of this concept and a number of simplifying assumptions, the linear relation observed by Sehgal was derived. 37 However, additional factors give much more weight to an approach based on chemical kinetics of condensation as discussed below. Figure 3 shows the influence of mean residence time on the exhaust particle size.…”

Section: Effect Of Pressure and Residence Timementioning

confidence: 99%

Performance of solid propellants containing metal additives

Cheung

Cohen

1965

AIAA Journal

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Test firings of solid propellant research rockets were made to study effects of propellant composition, pressure, and engine size on the exhaust oxide particle size, and on the composition of the solid exhaust products. The experimental results of this work and those reported by others were analyzed collectively to provide a reasonable description of the aluminum combustion and oxide condensation processes in solid propellant rocket motors. Combustion of aluminum was found to occur in the vapor phase, and was essentially complete in the engines studied although some combustion took place in the nozzle. The experimental results indicate that condensation of the oxide vapor can be described by first-order chemical kinetics. Further particle growth by agglomeration appears likely. The effect of two phase flow was found to be significant in the motors tested and reached a maximum in motors of a certain size. In motors where this loss is large, significant improvement in delivered performance can be realized by reducing the aluminum content.

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On the performance of solid propellants containing metal additives

Cited by 8 publications

References 4 publications

Removing hydrochloric acid exhaust products from high performance solid rocket propellant using aluminum-lithium alloy

Removing hydrochloric acid exhaust products from high performance solid rocket propellant using aluminum-lithium alloy

Overview of a Supersonic Probe for Solid Propellant Rocket CCP Collection

Performance of solid propellants containing metal additives

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