Abstract: 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%/.degree. F. is provided. 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 not more than 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.

Abstract: An inflatable shroud allows a propulsion system that is stored in fixed length and diameter cylinders or silos to occupy all of the available packaging length. When inflated the shroud provides the desired aerodynamic shape to reduce drag and improve performance. The inflatable shroud may be used on any aerodynamic structure that would benefit from an improved aerodynamic shape.