POLYSILOXANE-BASED INHIBITION SYSTEM FOR DOUBLE-BASE ROCKET PROPELLANTS

Four hydroxy-terminated poly( dimethyl siloxane) (HTPDMS) prepolymers of varying viscosities and molecular weights were prepared and used wi th and without alumina trihydrate as a filler. The HTPDMS viscosity an d filler percentage were optimized to ensure acceptable pot life and m echanical properties. Low nitroglycerine migration from the propellant to the inhibitor, excellent temperature stability, and good bonding b etween the propellant and inhibitor at temperature extremities (-40 to +60 degrees C) are some of the remarkable features of a room-temperat ure vulcanizing (RTV) silicone inhibitor. Double-base (DB) propellant grains were inhibited by a casting technique using Siloxane-15 and sta tically fired in a rocket motor. A smooth pressure-time profile infers that Siloxane-15 works satisfactorily as an inhibitor for DB propella nts. (C) 1998 John Wiley & Sons, Inc.