The effect of curing agents on solid composite rocket propellant characteristics
Rodiæ Vesna, BSc (Eng)[1])
Mirjana Petriæ, MSc (Eng)1)
Three different
types of curing agents have been discussed in this work, along with their
effects on viscosity, maximum stress, strain at maximum load and on the level of
burning rate and pressure exponent in the burning rate law of composite rocket
propellants.
Dymeril-diisocyanate, isophorone-diisocyanate and toluene-diisocyanate curing
agents were used. Hydroxyterminated polybutadiene is used as binder matrix,
bimodal mixture of ammonium-perchlorate (ratio 70:30) as oxidant and mixture of
aluminium powder (ratio 50:50) as metal component.
Key words: composite rocket propellant, curing agents, dymeril-diisocyanate, isophorone-diisocyanate, toluene-diisocyanate, hydroxyterminated polybutadiene, ammonium-perchlorate, viscosity, maximum stress, burning rate, pressure exponent.