Oxidizer Size Distribution Effects on Propellant Combustion

Renie, J.; Condon, J.A.; Osborn, J. R.

doi:10.2514/3.61240

Cited by 46 publications

(10 citation statements)

References 5 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The pressure-exponent values ν along with their pressure ranges and burning rate u(p) ranges of the most prominent plateau-burning formulations are listed in Table 3. In almost all the cases where a low pressure exponent is observed in the low-to-mid-pressure range (3)(4)(5)(6)(7)(8), the pressure range overlaps with that of the mid-pressure extinction of the corresponding matrix contained in the propellant [13]. This low pressure exponent is referred to as the "low-pressure plateau."…”

Section: Propellant Burning Ratesmentioning

confidence: 91%

See 1 more Smart Citation

Ammonium perchlorate-based composite solid propellant formulations with plateau burning rate trends

Banerjee

Chakravarthy

2007

Combust Explos Shock Waves

View full text Add to dashboard Cite

This paper presents burning rates as a function of pressure of several propellant formulations based on ammonium perchlorate (AP) and hydroxyl-terminated polybutadiene cured by isophorone diisocyanate, many of which exhibit significantly low (nearly zero or negative) values of the pressure exponent of the burning rate in distinct pressure ranges, termed as plateau burning rate trends. The propellants contain a bimodal distribution of AP particles with the size of the coarse and fine particles within narrow ranges whose mean values are widely separated. Two mean sizes of fine particles were considered for the propellant formulations in the present work, namely, 5 and 20 µm. These choices are based on the mid-pressure extinction behavior exhibited by the matrix of fine AP and binder contained in the propellants but when tested alone over a wide range of fine AP size and pressure. The propellants that include the fine AP/binder matrixes exhibiting a mid-pressure extinction, in turn, exhibit the plateau burning rate trends within the corresponding pressure ranges. A plateau is also observed at elevated pressures in the burning rates of some formulations, which is related to the diminishing relative importance of the near-surface leading-edge region of the oxidizer/fuel diffusion flame in the gas-phase combustion zone. The choice of the coarse AP size influences the exact pressure range within the mid-pressure extinction domain of the matrix where the propellant exhibits the plateau burning rate trends.Key words: composite solid propellants, plateau burning rate trends, mid-pressure extinction, bimodal distribution.It is well known [1] that a low value of the pressure exponent of the burning rate of a solid propellant is desirable to improve the design margin of solid rocket motors. A low (zero or negative) value of the pressure exponent also reduces the sensitivity of the pressure developed in the combustion chamber of the rocket motor to the initial temperature of the propellant. Quasisteady homogeneous one-dimensional (QSHOD) analy-

show abstract

Section: Propellant Burning Ratesmentioning

confidence: 91%

“…The binder melt flow was not considered to play a role in the observed behavior. These works [6,7] were primarily performed to examine and extend the validity of the petite ensemble model [8].…”

mentioning

confidence: 99%

Ammonium perchlorate-based composite solid propellant formulations with plateau burning rate trends

Banerjee

Chakravarthy

2007

Combust Explos Shock Waves

View full text Add to dashboard Cite

show abstract

“…Instances of different particle sizes and bin cutoffs are shown in Figure 4 and Figure 5. Of note is the log scale in the AP bin size, as the effect of particle size on pressure exponent is greater at smaller particle sizes, so smaller bins are used at smaller particle sizes [28]. This binning process removes some granularity in the regression function as it groups somewhat dissimilar particle sizes, but it provides access to features that provide insight into multi‐modal microstructural information.…”

Section: Data Collection and Curationmentioning

confidence: 99%

Prediction of Solid Propellant Burning Rate Characteristics Using Machine Learning Techniques

Klinger¹,

Casey

Manship

et al. 2023

Propellants Explo Pyrotec

View full text Add to dashboard Cite

When formulating a new solid propellant, one of the most important aspects of its performance is the burning rate's response to a change in pressure. For this reason, it is useful to be able to predict the burning rate response of a given propellant before the propellant formulation is created such that experimental trade studies are minimized or reduced in scale. While many theoretical and phenomenological models have been proposed to explain various aspects of energetic material combustion, little work has been made publicly available in the application of machine learning models to predicting solid propellant burning rates. To facilitate model creation, the material formulation and burning rate parameters for over 600 publicly available propellant formulations have been collected into a coherent data set. This work utilizes the large amount of publicly available data to inform a random forest machine learning (ML) model in the prediction of solid propellant burning rate parameters. This ML model operates over a large parameter space including ammonium perchlorate composite, plastic bonded high explosive, and double-base propellants. The model's accuracy, adaptability, and prediction capabilities are presented and discussed. The effects of different materials on a propellant's expected burning rate are examined.

show abstract

“…Common formulations for AP composite propellants include hydroxyl-terminated polybutadiene (HTPB) as ab inder and fuel, ac urative/plasticizer to solidify the HTPB binder,s ometimes aluminum particles as fuel to increase energy density,a nd sometimes am etal oxide additive to catalyze AP thermal decomposition [1].T he burning rate of AP composite propellants has been shown to be controlled by the concentration of AP,t he size of AP particles, binder type, the type and concentration of any catalyst additives, and the concentration and particle size of any added aluminum fuel (e.g.,R efs. [1][2][3][4][5][6][7]);h ence, AP composite propellants can be manipulated for burning rate tailoring by simply altering the proportions of the components and using small percentages of additives which can act as catalysts for condensed and/or gas-phase reactions, ignition sources, and/or provide thermal feedback or sinks.…”

Section: Introductionmentioning

confidence: 99%

Iron Nanoparticle Additives as Burning Rate Enhancers in AP/HTPB Composite Propellants

Styborski

Scorza

Smith

et al. 2014

Propellants Explo Pyrotec

View full text Add to dashboard Cite

a] 1I ntroductionAmmonium perchlorate (AP) composite propellants are widely used in solid rocket propulsion. Common formulations for AP composite propellants include hydroxyl-terminated polybutadiene (HTPB) as ab inder and fuel, ac urative/plasticizer to solidify the HTPB binder,s ometimes aluminum particles as fuel to increase energy density,a nd sometimes am etal oxide additive to catalyze AP thermal decomposition [1].T he burning rate of AP composite propellants has been shown to be controlled by the concentration of AP,t he size of AP particles, binder type, the type and concentration of any catalyst additives, and the concentration and particle size of any added aluminum fuel (e.g.,R efs. [1-7]);h ence, AP composite propellants can be manipulated for burning rate tailoring by simply altering the proportions of the components and using small percentages of additives which can act as catalysts for condensed and/or gas-phase reactions, ignition sources, and/or provide thermal feedback or sinks.The majority of work focused on catalyst additives for adjusting AP composite propellant burning rate has focused on metal oxides [5-20] (e.g.,F e 2 O 3 ,C uO, TiO 2 )w here metal oxides catalyze the thermal decomposition of AP and therefore increase the burning rate of AP composite propellants. Ferric oxide (Fe 2 O 3 )h as found the most use in commercial AP composite propellants due to its low cost, ease of manufacture, stability/inertness, and ability to generate high and reproducible burning rates [15].T he influence of the size of the catalyst particles has also been considered, where it is thought that smaller particles (e.g., nanoparticles) with higher surface-to-volume ratios have greater catalytic activity.H owever,n anoparticles can be dif-ficult to uniformly introduce into as olid propellant as they tend to agglomerate due to van der Walls and electrostatic forces.An abundance of literature also exists on the use of aluminum as fuel in AP composite propellants (e.g.,R efs. [21][22][23][24]), either as in nanoparticles or micro-sized particles, where aluminum increases energy density and can increase burning rate. Jayaraman et al. [24] have shown that aluminum nanoparticles can increase the burning rate of AP/ HTPB/Al propellants by up to 100 %compared to micro-aluminum. However,J ayaraman et al. also found the effect of Fe 2 O 3 additives as catalysts is mitigated for AP/HTPB/nano-Al propellants relative to AP/HTPB/micro-Al formulation (i.e.,n oa dditional burning rate increase is observed when adding Fe 2 O 3 to propellants containing Al nanoparticles).Interestingly,w ea re not aware of any literature in which iron (Fe) nanoparticles have been investigated as additives for AP compositep ropellants. Fe nanoparticles have several properties that could be advantageous as additives to AP composite propellants. Fe nanoparticles that have been exposed to air have an oxidized Fe 2 O 3 shell which can provide catalysis to AP decomposition at the propellant burning surface in the same manner as purely Fe 2 O 3 particle...

show abstract

Oxidizer Size Distribution Effects on Propellant Combustion

Cited by 46 publications

References 5 publications

Ammonium perchlorate-based composite solid propellant formulations with plateau burning rate trends

Ammonium perchlorate-based composite solid propellant formulations with plateau burning rate trends

Prediction of Solid Propellant Burning Rate Characteristics Using Machine Learning Techniques

Iron Nanoparticle Additives as Burning Rate Enhancers in AP/HTPB Composite Propellants

Contact Info

Product

Resources

About