Studies on Composite Extrudable Propellant with varied Burning Rate Pressure Index 'n'
AbstractThis paper discusses the development of composite propellantextrusion technique and the study of burning rate pressure indices nwith respect to compositional variations. The n is found to vary from0.35 to plateau and plateau to mesa by suitable compositionalmodifications. Compositional influence on burning rate with specificreference to plateau and mesaburning additives is described. Detailsof the process parameters like fluidity of the slurry, extrusion pressure,extrusion rate and die-swell are presented. This propellant is based onISRO-CTPB binder using ISRO-AP as oxidizer. Ammonium perchlorate (AP) particle size variation and inclusion of additives likePVC, lead stearate, ammonium sulphate, lithium fluoride etc. are foundto influence the burning rate pressure index n.
Gotzmey Carl & Seiden Nat,New binder system for composite solid propellants, AGARD-259, Naval Surface Weapons Centre and Naval Ordnance Station, USA, 1975.
Christenson, W.N., Development of an acoustic emission strand burning technique for motor burning rate prediction, AIAAISAE 14th Joint Propulsion Conference, Las Vegas, 25-27 July, 1978.
McCulloch, Charles R. and Moy, Bertram K., Mesa burning gas generator propellants, (Shalimar, Fla and Thomas C. Randle Oxom, Hill, USA), US Patent No. 3, 725, 154, 3 April, 1973.
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