Castable silicone based magnesium fueled propellant

Claim 1

A castable solid propellant composition suitable for use as a fuel generator for a ducted rocket motor, said composition comprising by weight (a) from about 50% to about 55% of spherical magnesium having a particle size range from about 44 microns to about 500 microns, and from about 5% to about 13% of flake magnesium having a particle size range such that 100% passes through 40 mesh and about 98% passes through 325 mesh U.S. Standard Sieve Series, the combined percentages of spherical magnesium and flake magnesium being from 55% to about 63% by weight of the propellant composition, and (b) from about 18% to about 25% of solid oxidizer of which at least about 80% is ammonium perchlorate, and (c) from about 16% to about 20% of a polysiloxane binder comprising a polysiloxane polymer having a viscosity measured at 77° F. of from about 12 poise to about 50 poise, and a cross-linking agent for said polysiloxane polymer, the weight ratio of solid oxidizer to polysiloxane polymer being from about 0.9/1 to about 1.5/1.