초록 ▼

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-b

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-s/lb) to about 275 (lb-s/lb), 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-1,2,3[bis(1,2-difluoroamino)ethoxy]propane (TVOPA), and a processing aid of lecithin.

대표청구항 ▼

An azido-based solid propellant composition having an improved burning rate comprising: a high energy plasticizer of tris-1,2,3[bis(1,2-difluoroamino)ethoxy]propane in an amount from about 24 to about 30 weight percent of said propellant composition; a curative and crosslinking agent of 4,5-epoxycyc

An azido-based solid propellant composition having an improved burning rate comprising: a high energy plasticizer of tris-1,2,3[bis(1,2-difluoroamino)ethoxy]propane in an amount from about 24 to about 30 weight percent of said propellant composition; a curative and crosslinking agent of 4,5-epoxycyclohexylmethyl 4′5′-epoxycyclohexylcarboxylate in an amount from about 0.75 to about 1.5 weight percent of said propellant composition; a carboranyl burning rate catalyst of carboranylmethyl propionate in an amount from about 2 to about 6 weight percent of said propellant composition; graphite linters of about 100 micrometers lengths in an amount from about 1 to about 3 weight percent of said propellant composition; aluminum powder in an amount from about 10 to about 12 weight percent of said propellant composition; aluminum flake in an amount from about 0.5 to about 2 weight percent of said propellant composition; ammonium perchlorate of about 0.9 micrometer diameter in an amount from about 46 to about 52 weight percent of said composition; a processing aid of lecithin in an amount from about 0.1 to about 0.2 weight percent of said propellant composition; and a binder of 2-azidoethyl acrylate-acrylic acid copolymer in an amount from about 3 to about 8 weight percent of said propellant composition.