HIGH PRESSURE, HIGH PERFORMANCE SOLID ROCKET HYDROXY-TERMINATED POLYBUTADIENE PROPELLANT FORMULATIONS

摘要

A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi over a substantial portion of a pressure range of about 1,000 psi to about 7,000 psi and a temperature sensitivity of less than about 0.15 %/ DEG F is provided. The solid propellant formulation contains from 35 % to 55 % by weight ammonium perchlorate particles having an average size of 200 mu m, from 25 % to 40 % by weight ammonium perchlorate particles having an average size in the range of from 2 mu m to 50 mu m, from 7 % to 10 % by weight hydroxy-terminated polybutadiene binder and at least one member selected from the group consisting of a co-oxidizer, a ballistic additive, and a polyisocyanate curative. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate of about 2 to about 3 mils per second during motor operation. The solid rocket propellant formulation can be cast in a grain pattern such that an all-boost thrust profile is achieved.