ANALYSIS OF THERMOPLASTIC PROPELLANTS BASED ON A PEBA BINDER SYSTEM

The objective of this paper is to present a new binder system that can be applied in composite rocket propellants to improve the properties of these propellants, not only for better performance but also to reduce waste and pollution. This novel system is based on the oxygenated thermoplastic elastomer (TPE) binder, which consists of a multi-block segmented polyether-b-block amide (PEBA) copolymer (alternating hard and soft segments) with the addition of a plasticizer, wetting agent, and an anti-oxidant. A series of tests were conducted to determine the properties of solid rocket propellants based on this binder system. The effect of the novel TPE binder system on the burning rate and mechanical properties of ammonium perchlorate (AP)-based propellants is demonstrated. Also, the thermal behavior of these propellant compositions was studied. The results show that propellants based on the novel TPE binder have a better energy performance than today's workhorse hydroxyl-terminated polybutadine/AP propellant, possess appropriate mechanical properties, and exhibit good processing and aging characteristics at low cost.