Aluminized plateau-burning solid propellant formulations and methods for their use

摘要

Solid rocket motor propellants which burn at at least one stable burn rate over at least one corresponding pressure range (i.e the burn rate v. pressure curve contains at least one area of low pressure exponent with respect to a normal curve) are described. The propellant compositions comprise a binder, from about 65% to about 90% by weight ammonium perchlorate, the ammonium perchlorate being of at least two distinct particle sizes; from about 0.3% to about 5.0% by weight refractory oxide selected from the group consisting of TiO.sub.2, Al.sub. 2 O.sub.3, SiO. sub.2, SnO.sub.2, and ZrO.sub.2 ; and from about 5 to about 25% by weight metal, such as aluminum.