Thiokol Corporation

Superior Ballistics, Inc.

Other

Morton Thiokol Inc.

Robert B Smalley, Jr

Michael Lee McPherson

Larry W Poulter

Ronald W Nelson

Marvin C Hawkins

Steven R Wassom

Jesse F Scivally

John F Miller

Bert H Parry

Girard H Rapp

A firearm cartridge has a case configured with a relatively straight-walled portion and a shoulder portion for housing a quantity of propellant. The case further includes a neck for retaining a bullet. The straight-walled portion defines a base cavity having an interior base diameter. The interior base diameter is approximately twice or more the neck diameter. The diameter ratios of the base and neck optimize combustion efficiency to reduce heat and acceleration losses. The cartridge body cavity is sized and configured to contain a sufficient quantity of propellant such that igniting the propellant causes formation of a propellant plug having a diameter that is approximately the diameter of the bullet, and wherein the propellant plug shears free from unburned propellant that is disposed adjacent the relatively straight-walled body portion.

Firearm cartridge and case-less chamber

Passive coatings accelerate burning at interfaces between rapidly burning propellants and thermally conductive or endothermic inert surfaces. The coatings, useful in firearm cartridges, firearm chambers, and solid rocket motors, reflect infrared energy from the combustion gases to reduce heat loss to the case or chamber and to accelerate ignition of the propellant. The reflective coating has a thermal breakdown temperature higher than the propellant ignition temperature. Firearm cartridges and chambers may have radial shoulder configuration that focuses a shockwave below a bullet base to reduce heat loss to the bullet and support bullet retention in the neck for a longer period of time.

Passive coatings and improved configurations for gun cartridges, solid rockets, and caseless ammunition

A firearm cartridge has a case configured with a straight-walled portion and a radial shoulder for housing a propellant. The case further includes a neck for retaining a bullet. The straight-walled portion defines a base cavity having an interior base diameter. The interior base diameter is approximately twice or more the neck diameter. The diameter ratios of the base and neck optimize combustion efficiency to reduce heat and acceleration losses. The radial shoulder focuses a shockwave below a bullet base to reduce heat loss to the bullet and support bullet retention in the neck for a longer period of time. A thermally insulating coating is utilized to reduce heat loss to the case or chamber and accelerate ignition of the propellant.

A robust polyurethane liner is disclosed for solid propellant rocket motors which is insensitive to large variations in stoichiometry, exhibits increased cohesive strength and, when used in combination with a unique two coat (wet coat) liner process described below, modifies the ballistic properties of the adjacent interfacial propellant layer. The liner compositions include a polymeric binder having a plurality of reactive hydroxyl functional groups and a curing agent having a plurality of reactive isocyanate functional groups. The quantity of binder and curing agent is selected such that the NCO/OH ratio is in the range from 1.5 to 4.5. Diisocyanate curing agents are particularly useful. A bonding agent, such as a polyfunctional aziridine compound, is typically present in the liner composition in an amount ranging from about 3% to about 5%, by weight. An oligomer catalyst is included in the liner composition in an amount ranging from about 15% to about 50%, by weight. Diammonium phosphate ((NH.sub.4).sub.2 HPO.sub.4) functions as an oligomer catalyst and as a ballistic modifier to inhibit propellant burn rate when the liner is cured concurrently with the propellant. A colorant, such as rhodamine B, may optionally be included to assist in determining coverage or thickness of the liner coating.

Robust propellant liner and interfacial propellant burn rate control

A control system for use in missiles and other projectiles which provides pitch, yaw and roll control. The control system includes two opposing pairs of flaps configured in the aft end of the missile case. Each flap is attached for rotation about its leading edge. Prior to actuation, the flaps conform to the exterior surface of the missile. Upon actuation, the flaps extend into the airstream to induce aerodynamic forces. The axis of rotation of each flap is positioned at an oblique angle to the radial plane of the missile.

Finless aerodynamic control system

An apparatus is provided for the removal of oversized contaminants from particulate material the is particularly suitable for the removal of contaminants from low density, high surface area particulate materials. The removal of contaminants is accomplished during the transfer of the particulate material from its storage or transport container to a receiving container. The apparatus comprises an assembly having a weir, a trap disposed adjacent said weir, a screen o for separating particulate material from oversized contaminants, a baffle, and an opening through which particulate material will flow freely. The weir has a weir trap flange extending laterally from a weir wall. The trap is configured to capture contaminants if the container to which the assembly is secured is maneuvered to initiate the flow of the particulate material from the container to the receiving container. When so maneuvered, the lowermost portion of the trap in the proximity of the flow of the particulate materials subtends the weir. The screen permits particulate material trapped within the trap to pass therethrough so that the container can be completely emptied of particulate material while separating and capturing oversized contaminants. The baffle is spaced from the weir and disposed to deflect the flow of the particulate material towards the trap. The flow of particulate material follows a tortured path around the baffle and over the weir to exit the container through the opening.

Apparatus for removing contamination from low density particulate

Apparatus useful on space vehicles as a valve for establishing external pressure in a pressure container or otherwise as an engine for performing work. The apparatus is responsive to atomspheric pressure retained in a plenum are applied to one side of a piston which atomspheric pressure is greater than an external pressure applied to the other side of the piston in a vacuum environment. A method for operation of such apparatus is also disclosed.

Growing community of inventors

Brigham City, UT, United States of America

Robert B Smalley, Jr