DEPARTMENT OF THE ARMY WASHINGTON DC
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A high energy, high performance, ultrahigh-burning rate composite propellant results when 2-azidoethyl acrylate is copolymerized with acrylic acid and is employed as the binder system for the composite propellant. The energetic binder when used in an amount of about 4.25 weight percent of an azido-based propellant composition as compared to a ethyl acrylate binder system results in a specific impulse increase from about 264 lb-slb to about 275 lb-slb, and a burning rate increase from about 13.7 ips to about 19.8 ips at 1000 psia, and a burning rate increase from about 21.6 ips to about 30.2 ips at 2000 psia. The other propellant ingredients comprise a high solids loading of ammonium perchlorate, aluminum flake and aluminum powder, a burning rate catalyst of carboranylmethyl propionate, graphite linters, the crosslinking and curing agent 4,5-epoxycyclohexylmethyl 4,5-epoxycyclohexylcarboxylate ERL-4221, tris-1,2,3bis1,2-difluoroaminoethoxylpropaneTVOPA, and a processing aid of lecithin.
- Solid Rocket Propellants