Gas phase flame structure of solid propellant sandwiches with different reaction mechanisms

Gaduparthi, Trinath; Pandey, Manish; Chakravarthy, Satyanarayanan R.

doi:10.1016/j.combustflame.2015.10.028

Cited by 25 publications

(5 citation statements)

References 30 publications

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“…As the temperature continues to increase, the lattic stable and melts at approximately 725-825 K [30], followed by an exoth from AP dissociation, sublimation, and decomposition. Roughly 30% of sublimation and evaporation, which produces NH3 and HCLO4, while the r decomposes on the surface, resulting in an exothermic condensed-phase re sulting product then undergoes a series of chain reactions to form a premi overall process of the AP condensed-phase decomposition can be expres [31]: AP → 0.3(NH3 + HClO4) + 0.7(1.5H2O + 1.25O2 + HCl + 0.5 N HTPB is supposed to release C4H6 in the gas phase, according to the f tion [32][33][34]:…”

Section: Solid Phasementioning

confidence: 99%

“…HTPB is supposed to release C 4 H 6 in the gas phase, according to the following reaction [32][33][34]:…”

Section: Solid Phasementioning

confidence: 99%

“…Both the pre-exponential term A and the activation energy E are empirical constants. The thermodynamic data of AP and HTPB are shown in Table 1, primarily derived from reference [19,32]. The burning rate of pure AP is measured at 3.3 mm/s and the surface temperature at 850 K for 2.07 MPa, according to reference [35,36].…”

Section: Solid Phasementioning

confidence: 99%

“…As detailed data for chemical kinetics in flames are often not available at high pressures and are more complex and costly to obtain, this paper employs a simplified 12-species and three-step global mechanism, which can accurately describe the flame structure, the composition of products for the reactions is obtained using the chemical equilibrium code NASA SP273, the product species considered here constitute more than 95% of all the predicted species [32][33][34]. (9) The reaction rates of the aforementioned reactions are determined by a pressuredependent Arrhenius equation expressed as [40]:…”

Section: Gas Phase 231 Global Kinetic Modelmentioning

confidence: 99%

See 3 more Smart Citations

Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant

Sun

Liu

et al. 2023

Aerospace

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A gas–solid-coupled sandwich combustion model was established for ammonium perchlorate (AP)/hydroxyl-terminated polybutadiene (HTPB) composite propellant. Numerical simulations were conducted to investigate the influence of the content of AP and the relative position of the coarse AP on the flame structure and the burning rate of the propellant. The results indicated that the overall AP mass fraction has a significant effect on the gas-phase flame temperature and burning rate, and there exists an optimal oxygen-to-fuel ratio that maximizes the burning rate. As the mass fraction of fine AP increased, the premixed flame above the binder matrix gradually took over the dominance of the diffusion flame, and the intensity of the diffusion flame near the interface of coarse AP and binder matrix also increased, resulting in a significant increase in the burning rate. As the mass fraction of fine AP increases from 0% to 70.0%, the average surface temperature increases from 937 K to 1026 K, and the burning rate rises from 0.9 cm/s to 2.7 cm/s. The location of the coarse AP causes the flame tilts to the side with less binder matrix, but it had little effect on the burn rate of the propellant.

show abstract

Section: Solid Phasementioning

confidence: 99%

“…HTPB is supposed to release C 4 H 6 in the gas phase, according to the following reaction [32][33][34]:…”

Section: Solid Phasementioning

confidence: 99%

Section: Solid Phasementioning

confidence: 99%

Section: Gas Phase 231 Global Kinetic Modelmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant

Sun

Liu

et al. 2023

Aerospace

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show abstract

“…Further, the diffusion and premixed dual flame appears when the pressure drops to about 1.7 MPa [10]. For the same AP/HTPB system, three different reaction mechanisms have been proposed and simulated, which are based on the global chemistry using symbolic species for the three flames, a 12-species mechanism, and a 72-step reaction mechanism with 39-species, respectively [11]. Except for the numerical simulations, the chemical structure of the propellant flame could be predicted by ReaxFF reactive force field molecular dynamics and equilibrium thermodynamics simulations [12].…”

Section: Introductionmentioning

confidence: 99%

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Li¹,

Liu

Fu³

et al. 2019

Nanomaterials

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In this paper, the dependences of the morphology, particle sizes, and compositions of the condensed combustion products (CCP) of modified double-base propellants (1,3,5-trimethylenetrinitramine (RDX) as oxidizer) on the chamber pressure (<35 MPa) and nickel inclusion have been evaluated under a practical rocket motor operation. It has been shown that higher pressure results in smaller average particle sizes of the CCPs. The CCPs of Ni-containing propellants have more diverse morphologies, including spherical particles, large layered structures, and small flakes coated on large particles depending on the pressure. The specific surface area (SSA) of CCPs is in the range of 2.49 to 3.24 m2 g−1 for propellants without nickel are less dependent on the pressure, whereas it is 1.22 to 3.81 Ni-based propellants. The C, N, O, Al, Cu, Pb, and Si are the major elements presented on the surfaces of the CCP particles of both propellants. The compositions of CCPs from Ni-propellant are much more diverse than another one, but only three or four major phases have been found for both propellants under any pressure. The metallic copper is presented in CCPs for both propellants when the chamber pressure is low. The lead salt as the catalyst has been transformed in to Pb(OH)Cl as the most common products of lead-based catalysts with pressure lower than 15 MPa. When pressure is higher than 5 MPa, the nickel-based CCPs has been found to contain one of the following crystalline phases: Pb2Ni(NO2)6, (NH4)2Ni(SO4)2·6H2O, C2H2NiO4·2H2O, and NiO, depending on the pressure.

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Combustion Organization of Micro-Solid Rocket Motor

Hu,

Liu,

Zhang

et al. 2024

Space Technology Library

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Gas phase flame structure of solid propellant sandwiches with different reaction mechanisms

Cited by 25 publications

References 30 publications

Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant

Numerical Investigation on the Effect of Ammonium Perchlorate Content and Position on the Combustion Characteristics of an Ammonium Perchlorate/Hydroxyl-Terminated Polybutadiene Propellant

Transformation of Combustion Nanocatalysts inside Solid Rocket Motor under Various Pressures

Combustion Organization of Micro-Solid Rocket Motor

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