| || On Performance Evaluation of a New Liquid Propellant
Author : Panda, S.P.;Kulkarni, S.G.;Kakade, Seema D.;Tiwari, S.P.;Rao, K.P.
Source : Defence Science Journal ; Vol:36(1) ; 1986 ; pp 1-8
Subject : 66 Chemical Technology;662.3 Propellants
Keywords : 3 Carene;RFNA;Hypergolic ignition;Propellant
Abstract : A blend of 3-carence and cardanol in 70:30 weight proportion exhibits synergistic hypergolic ignition with red fuming nitric acid (RFNA) as oxidizer. Attempts have been made to evaluate this new propellant by theoretical calculation of performance parameters and verification of the results by static firing of a 10kg thrust rocket motor around 20 atmospheres of chamber pressure. At an oxidizer-to-fuel weight ratio (o/f) of 3.34 (RFNA) used had 21% N/sup 2/ O/sup 4/ and 5% by weight of concentrated sulphuric acid as catalyst), the propellant produced a reasonably smooth pressure-time curve with an ignition delay of 35 milliseconds. The theoretical characteristic velocity value matched well with the experimental. No carbon residue was left in the rocket motor after firing. Specific impulse (theoretical) of the propellant has been found to be 223.8 seconds at chamber pressure, 20 atmos and exist pressure, 1 atmos.