Abstract: A linerless rocket motor is provided by the bonding of a reticulated support structure, which is embedded in an homogenous mass of propellant material including an oxidant, to the inner wall of the rocket motor case. An inexpensive, safe, and easy to manufacture igniter is comprised of an homogeneous mass of propellant material including an oxidant and a reticulated support structure embedded therein. A light weight, high crush strength, and high strain capability sliver for a rocket motor comprises a block of inert material and a reticulated support structure of carbon, graphite, or a non-combustible material embedded therein. A rocket motor is prevented from accidental propulsion during a fire by attaching a propellant block to the outer side of the rocket motor base. The propellant block burns and produces heat during the fire to weaken the motor case so that pressure resulting from burning of propellant in the rocket motor will burst a hole in the rocket motor case to relive the pressure.

Abstract: A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

Abstract: A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

Abstract: A solid propellant grain which comprises an homogeneous mass of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure in a portion only of the propellant mass. The reticulated structure may be coated with a high thermal conductivity material to provide an increased burning rate. The coat of material is selected to preferably provide improved bonding to the propellant mass.

Abstract: An elastomeric composition suitable for use as a rocket motor case insulation is disclosed. The composition comprises a vulcanizable elastomeric material and reinforcing polybenzimidazole polymer fibers in combination with a powder filler. A preferred embodiment utilizes polyisoprene as the elastomer and silica as the powder filler. These compositions have better erosion resistance than asbestos-reinforced compositions, and do not pose the environmental or safety risks associated with asbestos-reinforced insulation.

Abstract: Bonding of hydroxy terminated polybutadiene based propellant grains to rocket motor liners and of the liner to the motor case is greatly improved by incorporating an aziridine in a urethane cured hydroxy terminated polybutadiene based liner.

Abstract: A technique for improving the processibility of composite propellants through reduction of the catalytic effect of iron oxide upon the polymer/curing agent reaction.

Abstract: Finely divided aluminum oxide increases the burning rate, reduces the pressure exponent at high pressures and stabilizes the combustion of solid propellant compositions.