| || Studies on Composite Extrudable Propellant with Varied Burning Rate Pressure Index n
Author : Varghese, T.L.;Muthiah, Rm.;David, John;Kurian, A.J.;Athithan, S.K.;Krishnamurthy, V.N.;Kurup, M.R.
Source : Defence Science Journal ; Vol:39(1) ; 1989 ; pp 1-12
Subject : 66 Chemical Technology;662.3 Propellants
Keywords : Composite propellant extrusion technique;Burning rate pressure;Mesaburning additives
Abstract : This paper discusses the development of composite propellant extrusion technique and the study of burning rate pressure indices n with respect to compositional variations. The n is found to vary from 0.35 to plateau and plateau to mesa by suitable compositional modifications. Compositional influence on burning rate with specific reference to plateau and mesaburning additives is described. Details of the process parameters like fluidity of the slurry, extrusion pressure, extrusion rate and die-swell are presented. This propellant is based on ISRO-CTPB binder using ISRO-AP as oxidizer. Ammonium per chlorate (AP) particle size variation and inclusion of additives like PVC, lead stearate, ammonium sulphate, lithium fluoride etc. are found to influence the burning rate pressure index n.