Thiokol Corporation

Morton Thiokol Inc.

William H Graham

Inella G Shepard

James D Byrd

J B Canterberry

Kenneth E Junior

Robert E Askins

Carl M Rector

Robert L Stanley

Joey M Reed

Kenneth E Bevel

Theodore S Sumrail

Liquid nitromalonate polyesters and methods for their preparation are disclosed. Solid propellants are provided which employ as the binder a nitromalonate polyester. These propellants are resistant to plasticizer syneresis and crystallization and provide an increase in the specific impulse of the propellant.

Energetic nitro malonate polyester binders

An insensitive high explosive is obtained by using a dicyandiamide (DCDA), ammonium nitrate (AN), guanidine nitrate (GN), ethylene diamine dinitrate (EDDN) eutectic melt binder in combination with ammonium perchlorate (AP) oxidizer, fine RDX (1 .mu.m to 10 .mu.m particle size), and aluminum metal as a fuel. The fine RDX particles improve performance, boosterability, and sensitivity. The inclusion of AP greatly improves air blast by adding oxygen to the reaction and insuring complete combustion of the ingredients. The aluminum extends the pressure pulse. The ratio of materials is formulated to obtain the lowest known processing temperature.

Aluminized eutectic bonded insensitive high explosive

Compositions and methods for increasing the storage life of a propellant grain by reducing the rate of decomposition of its nitrate ester components. A nitrate ester stabilizer is placed in a layer adjacent to a nonburning surface of the propellant grain. The stabilizer migrates from the layer into the grain's nonburning surface to provide additional stabilization for the entire grain, especially portions of the grain adjacent to the protected nonburning surface.

Nitrate ester stabilizing layer for propellant grain

Process for forming a liner and cast propellant charge in a rocket engine casing without separately precuring the liner, comprising the steps of providing a blocked curable liner composition which is the reaction product of a prepolymer, an isocyanate curing agent, and a blocking agent; applying the liner composition to an internal surface of a rocket casing; preheating the casing and liner assembly to simultaneously prepare the assembly for receiving a propellant, unblock the liner, and precure the liner to a tacky state; casting the propellant change into interfacial contact with the liner; and cocuring the liner and propellant compositions. The blocked, curable liner composition has a very long pot life which is terminated by heating the composition sufficiently to uncouple the blocking agent from the isocyanate curing agent and initiate a rapid cure. The liner composition does not require precuring, as it is unblocked by preheating the liner and rocket casing sufficiently to receive to cast propellant. The blocked liner composition has the following structure. ##STR1##

Process for forming a liner and cast propellant charge in a rocket motor

Salicylate esters have been found to be suitable blocking agents for polyisocyanates, enabling preparation of hydroxy terminated polybutadiene based polyurethane bound propellant grains having extended pot life. Unblocking occurs readily at normal propellant cure temperatures, allowing normal cure rates.

Hydroxy terminated polybutadiene based polyurethane bound propellant

Curing catalysts comprising organo metallic compounds, and carboxylic acids or compounds convertible thereto, processes for their use and compositions containing them are disclosed. The compositions enable the control of the curing rate profile of hydroxy terminated polybutadiene based urethane propellant binders, and the cure rate profile of polyurethane resin systems generally.

Growing community of inventors

Huntsville, AL, United States of America

William H Graham