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Comparative Studies of Pressure Sensitization of Zirconium Carbide and Zirconium Silicate on Burning Rates in a RDX‐AP based Composite Propellant
Author(s) -
Singh Harmeet,
Upadhyay Jayesh,
Chimurkar Dhanraj,
Ghorpade Vishwas,
Kotbagi Amarnath,
Kumar Amit,
Kumar Arvind,
Gupta Manoj
Publication year - 2014
Publication title -
propellants, explosives, pyrotechnics
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.56
H-Index - 65
eISSN - 1521-4087
pISSN - 0721-3115
DOI - 10.1002/prep.201300042
Subject(s) - propellant , zirconium , materials science , composite number , zirconium carbide , carbide , exponent , silicate , rocket (weapon) , composite material , analytical chemistry (journal) , thermodynamics , metallurgy , chemistry , chromatography , organic chemistry , physics , linguistics , philosophy , engineering , aerospace engineering
In a systematic study to compare the effects of the values of burning rate and pressure exponent in RDX‐AP based composite propellant, various compositions with varying percentages of zirconium carbide (ZrC) and zirconium silicate (ZrSiO 4 ) were formulated to select a suitable candidate. Various rocket parameters of each formulation were theoretically predicted by the NASA CEC‐71 program and the burning rate was evaluated in pressure range of 3–11 MPa. In addition, density, sensitivity, and thermal properties of compositions having maximum effects on pressure exponent’s values were also evaluated. It was concluded that ZrSiO 4 enhances the pressure exponent “n” value substantially, whereas ZrC doesn’t have significant effects on it as compared to base composition and also provides higher density values of composite propellant formulated.