Combustion and Thermal Decomposition of a Binary Oxidiser System: Ammonium Perchlorate-Potassium Perchlorate

Seetharamacharyulu, D; Verneker, VR Pai; Mallya, R. M.

doi:10.1080/00102208108946969

Cited by 1 publication

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“…Recently, Ishitha et al [10,11] have also doped AP with small amounts of K + and observed an enhancement in the deflagration behaviour of AP, as the K + ions enhance the condensed phase decomposition of AP. Furthermore, Seetharamachayulu et al [12] have reported the effect of KP on the combustion and thermal decomposition of a binary oxidizer system based on AP and KP, and their findings revealed that the burning rate of the pellet increased up to 30% KP, and beyond this it decreased drastically [13]. Although a literature survey has revealed that the characteristics of complete KP-based composite propellant formulations are not very good from an applications point of view, due to solid residue in the nozzle exit, hygroscopicity and low heat of combustion, nevertheless KP based compositions offer high burning rates and high densities, and reduced combustion instability, which is one of the preferred criteria in the field of rocketry [14,15].…”

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confidence: 99%

Evaluation of Potassium Perchlorate as a Burning Rate Modifier in Composite Propellant Formulations

Jain

Mehilal

Singh

et al. 2016

Cent. Eur. J. Energ. Mater.

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Abstract:The burning rate of a solid composite propellant is one of its most important ballistic properties. To achieve a specified burning rate, transition metal oxides are used as burning rate modifiers. However, addition of transition metal oxides creates inertness in the composition. To avoid such inertness, an attempt has been made to incorporate potassium perchlorate (KP) as a burning rate modifier by partially replacing ammonium perchlorate (AP), up to the 10% level, and the composition was then studied in detail for its mechanical, thermal and ballistic properties. The data revealed that no change occurred in the case of the mechanical properties, however, the thermal stability decreased as the KP content was increased. The burning rate data revealed that on incorporation of 10% KP, there was an enhancement in the burning rate of up to 35% in comparison to the original composite propellant formulation, but beyond this no enhancement in burning rate was observed, indicating that the optimum content for KP in the composition had been reached.

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